Forging method of tc6 titanium alloy for aviation

Abstract

The present application relates to the field of titanium alloy preparation method for aviation, and particularly relates to a forging method for improving the mechanical properties of TC6 titanium alloy for aviation, which comprises the following steps: a. ingot blank pretreatment; b. placing the pretreated ingot blank in a resistance heating furnace, heating to T β +(100-160) DEG C at a heating rate of 5 DEG C / min to 10 DEG C / min; after each forging, forced air cooling is performed, when the cross-section equivalent diameter of the forging is less than or equal to 300 mm, a cooling rate of 2 DEG C / s to 5 DEG C / s is adopted; when the cross-section equivalent diameter of the forging is greater than 300 mm, hierarchical cooling is adopted; c. adopting sub-beta forging or super-beta forging to perform forging; d. heating the blank obtained in step c to T β -(30-70) DEG C, maintaining for 5 h to 7 h to ensure temperature uniformity; e. isothermal annealing is performed on the forging blank; after air cooling to room temperature, surface finishing and non-destructive testing are performed on the forging to ensure no cracks, inclusions and pores, and finally the finished forging of TC6 titanium alloy for aviation is obtained. The present application is particularly suitable for the forging of TC6 titanium alloy for aviation.

Description

Technical Field

[0001] This invention relates to the field of methods for preparing titanium alloys for aviation, and more particularly to a forging method for TC6 titanium alloy for aviation. Background Technology

[0002] TC6 titanium alloy is a martensitic α+β two-phase heat-resistant titanium alloy with low density, high strength, good plasticity and toughness, and excellent corrosion resistance. It is one of the main titanium alloys in the aerospace field and can be used to manufacture aero-engine parts that operate for long periods below 400°C and for short periods at 450°C.

[0003] Taking patent document CN120790815A as an example, it relates to a method for preparing a large-size forged plate of TC6 titanium alloy. The method includes the following steps: Initial forging: A large-size TC6 titanium alloy ingot is subjected to 1-3 upsetting and drawing forging passes. The first pass is a high-temperature homogenization treatment, with each pass heated to 60°C-200°C above the phase transformation point and held at that temperature before forging. After all passes are completed, the ingot is cooled to obtain a primary intermediate billet. Intermediate forging: The primary intermediate billet is subjected to 4-7 forging passes. Some passes are heated to 30°C-150°C above the phase transformation point and held at that temperature, while the remaining passes are heated to 20°C-60°C below the phase transformation point and held at that temperature. After all passes are completed, the ingot is cooled to obtain a secondary intermediate billet. Quasi-β forging: The secondary intermediate billet is heated to 10°C-40°C above the phase transformation point and held at that temperature, then subjected to one forging pass. After forging, the ingot is cooled to obtain an intermediate billet. Two-phase forging: The intermediate billet is heated 1-2 times, each time to 20°C-70°C below the phase transformation point and held at that temperature to obtain a forged plate. Overall heat treatment and machining: The forged plate is then heat-treated and machined to obtain the finished forged plate. However, this method involves repeatedly upsetting and drawing multiple times to break down the microstructure, resulting in a long production cycle, low yield, and high production costs. This is because repeated upsetting and drawing multiple times increases the difficulty of controlling the forging process, leading to poor batch stability of forgings, and making them prone to problems such as uneven grain size and internal defects. These issues affect the room temperature and high temperature mechanical properties of the forgings, and in severe cases, can even affect the service life and safety of aerospace components. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a forging method for TC6 titanium alloy for aerospace applications that improves the mechanical properties of forgings.

[0005] The technical solution adopted by this invention to solve its technical problem is: a forging method for TC6 titanium alloy for aerospace applications, comprising the following steps: a. Pretreatment of ingot billets: TC6 titanium alloy ingots were prepared by three-stage vacuum arc melting. At the end of the third vacuum arc melting, neodymium was added as a microalloying element in the form of Al-Nd master alloy at a mass percentage of 0.08% to 0.15%. The added neodymium was stirred to ensure uniform melting, and ingot billet was obtained. The surface of the ingot blank is ground to achieve a surface finish of ≤Ra1.6 μm, and then a ceramic high-temperature protective coating with a thickness of 0.1 mm to 0.3 mm is applied to the surface of the ingot blank. The ingot billet is placed in a resistance heating furnace and held at 880 ℃ to 920 ℃ for 12 h to 24 h. After the holding period, the furnace is cooled to below 500 ℃ and then air-cooled to room temperature. b. Place the pretreated ingot billet in a resistance heating furnace and heat it to T at a heating rate of 5℃ / min to 10℃ / min. β +(100-160) ℃; When the cross-sectional diameter of the ingot billet is less than 300 mm, the holding time is 3 to 5 hours. When the cross-sectional diameter of the ingot billet is greater than 300 mm, it should be kept at a temperature of 5 to 7 hours. After the heat preservation is completed, the ingot billet is taken out of the furnace. First, the edges and corners of the ingot billet are chamfered and upset flat. Then, it is forged by upset drawing combination forging for 1 to 3 times to draw and square the billet. The deformation amount per pass is 30% to 40%, the cumulative deformation amount is ≥60%, and the forging ratio is 1.4 to 2.0. Within the same firing cycle, the first drawing is radial drawing, and the second drawing is axial drawing. The axial drawing feed is 200 mm to 300 mm, and the drawing rate is 40 mm / s to 80 mm / s. Upsetting is done using slow hammer upsetting, with an upsetting rate of 10 mm / s to 20 mm / s. Forced air cooling is used after each forging cycle. When the equivalent diameter of the forging section is ≤300mm, a cooling rate of 2℃ / s to 5℃ / s is adopted; when the equivalent diameter of the forging section is greater than 300mm, staged cooling is adopted. c. Forging is carried out using sub-β forging or super-β forging. During the forging process, the drawing feed is 250 mm to 300 mm, the drawing rate is 40 mm / s to 80 mm / s, the deformation per pass is 25% to 45%, the cumulative deformation is ≥65%, the cross section of the forged billet is square, and the billet is air-cooled to room temperature after each forging. d. Heat the billet obtained from forging in step c to T. β -(30-70) ℃, keep warm for 5 to 7 hours to ensure uniform temperature; After heat preservation, the product is taken out of the furnace and then forged in one pass using straight drawing forging. The deformation amount of the single pass of the final forging is 12% to 25%, the drawing feed is 200mm to 250mm, and the drawing rate is 40mm / s to 80mm / s. During the final forging process, when the billet temperature is below 850 ℃, it is returned to the furnace for reheating to the set final forging temperature. The number of reheating times during the entire final forging process is ≤2 times, and each reheating is held for 1 h to 1.5 h. If the number of heating cycles exceeds 2 or a single heating cycle exceeds the time limit, the billet should be re-evaluated or scrapped. After final forging, the blank is air-cooled to room temperature to obtain a TC6 titanium alloy forging. e. The forging blank is isothermally annealed, then furnace cooled to 650 ℃ and held for 2 h, followed by air cooling to room temperature; After air cooling to room temperature, the forgings undergo surface finishing and non-destructive testing to ensure the absence of cracks, inclusions, and porosity, ultimately yielding finished TC6 titanium alloy forgings for aerospace applications.

[0006] Furthermore, for forgings with an equivalent cross-sectional diameter greater than 300 mm, the staged cooling process is as follows: first, strong air cooling at 3℃ / s to 5℃ / s to approximately 600℃, followed by air cooling to room temperature.

[0007] Furthermore, in step c, the sub-β forging method is: heating to T β -(40-60)℃, heat treatment for 7 to 9 hours, forging ratio 1.2 to 1.6, using flat square drawing.

[0008] Furthermore, in step c, the super β forging method is: heating to T β +(20-60) ℃, heat treatment for 4 to 6 hours, forging ratio 1.4 to 1.8, and diagonal drawing.

[0009] Furthermore, in step e, the forging blank is annealed isothermally at 860 ℃ for 1.5 h.

[0010] The beneficial effects of this invention are as follows: By adding a specific amount of neodymium (Nd) and simultaneously employing homogenization and a three-stage combined forging process, the grain size of TC6 titanium alloy is effectively refined, and abnormal growth of the α phase is suppressed, significantly improving the mechanical properties of forgings at both room temperature and high temperature. Employing sub-β or super-β dual-mode forging allows for flexible adaptation to different aerospace application requirements, solving the problems of large performance fluctuations and difficulty in balancing strength and toughness in traditional processes. Through refined parameter control throughout the entire process and strict temperature compensation limits, the quality stability and yield of forgings are improved, and the process requires no special equipment modification, combining innovation and industrial practicality to meet the stringent requirements of high-end TC6 titanium alloy forgings for aerospace applications. This invention is particularly suitable for the forging of TC6 titanium alloys for aerospace applications. Detailed Implementation

[0011] The forging method for aerospace-grade TC6 titanium alloy includes the following steps: a. TC6 titanium alloy ingots were prepared using a three-stage vacuum arc remelting process. At the end of the third stage of vacuum arc remelting, neodymium (Nd) at a mass percentage of 0.08% to 0.15% was added as a microalloying element in the form of an Al-Nd master alloy, and the mixture was thoroughly stirred to ensure uniform incorporation. The ingot billet was then surface-polished and refinished to remove surface defects, achieving a surface finish ≤ Ra 1.6 μm. Subsequently, a ceramic high-temperature protective coating with a thickness of 0.1 mm to 0.3 mm was applied to the billet surface. The billet was placed in a resistance heating furnace and held at 880 ℃ to 920 ℃ for 12 h to 24 h. After holding, the furnace was cooled to below 500 ℃, followed by air cooling to room temperature. This further eliminated component segregation in the ingot, improved microstructure uniformity, and promoted the uniform dispersion and distribution of Nd in the matrix, thus maximizing its microalloying effect.

[0012] b. Place the pretreated billet in a resistance heating furnace and heat it to T at a heating rate of 5℃ / min to 10℃ / min. β +(100~160) ℃, where T β The β-phase transformation temperature is set for this batch of TC6 titanium alloy. For billet sections with a diameter less than 300 mm, the holding time is 3 to 5 hours; for sections with a diameter greater than 300 mm, the holding time is 5 to 7 hours to ensure full heat penetration and uniform distribution of neodymium in the matrix, avoiding localized agglomeration. After holding, the billet is quickly removed from the furnace. The four corners of the billet are first chamfered and upset, then 1 to 3 passes of upsetting and drawing are used for square billet opening. The deformation per pass is 30% to 40%, with a cumulative deformation ≥ 60%, and a forging ratio of 1.4 to 2.0. Within the same pass, the first drawing is radial, and the second drawing is axial, with an axial feed of 200 to 300 mm and a drawing rate of 40 to 80 mm / s. Upsetting is done using slow, multi-hammer upsetting at a rate of 10 to 20 mm / s. Forced air cooling is used after each forging cycle. When the equivalent diameter of the forging section is ≤300mm, a cooling rate of 2℃ / s to 5℃ / s is adopted. For forgings with larger sections, staged cooling can be adopted: first, forced air cooling at 3℃ / s to 5℃ / s to about 600℃, and then air cooling to room temperature.

[0013] c. Based on the target performance of the forging, either sub-β forging or super-β forging is adopted: 1) Sub-β forging (advantages include high plasticity and high overall strength): heated to T β -(40~60) ℃, heat treatment for 7 h to 9 h, forging ratio 1.2 to 1.6, using flat square drawing; 2) Super β forging (advantages include high creep resistance and high fracture toughness): heated to T β+(20~60) ℃, heat preservation for 4h to 6h, forging ratio 1.4 to 1.8, and diagonal drawing.

[0014] In both sub-β forging and super-β forging modes, the drawing feed is 200 mm to 300 mm and the drawing rate is 40 mm / s to 80 mm / s; the deformation per pass is 25% to 45%, the cumulative deformation is ≥65%, and the cross-section of the forged billet is square; after each forging, it is air-cooled to room temperature. Neodymium can effectively inhibit the abnormal precipitation and growth of the α phase and ensure the uniformity of the forging structure.

[0015] d. Heat the secondary forging billet to T β -30~70℃, hold at this temperature for 5 to 7 hours to ensure uniform temperature and full utilization of neodymium. After holding, remove from the furnace and complete the final forging in one pass using direct drawing forging; the deformation per pass is 12% to 25%, the drawing feed is 200 mm to 250 mm, and the drawing rate is 40 mm / s to 80 mm / s. During the final forging process, if the billet temperature is below 850℃, it is allowed to return to the furnace for reheating to the set final forging temperature. The total number of reheating cycles should be ≤2, with each reheating holding time being 1 to 1.5 hours. If the number of reheating cycles exceeds 2 or the single reheating exceeds the time limit, the billet should be re-evaluated or scrapped to avoid increased surface oxidation, coarsening of the internal structure, and neodymium segregation caused by multiple thermal cycles. After the final forging is completed, air cool to room temperature to obtain TC6 titanium alloy forging blanks. The micro-alloying effect of neodymium can further improve the room temperature and high temperature mechanical properties of the forgings, meeting the stringent requirements of the aerospace industry.

[0016] e. The forging blank is subjected to isothermal annealing at 860 ℃ for 1.5 h, followed by furnace cooling to 650 ℃ and holding for 2 h, and then air cooling to room temperature. This process eliminates residual forging stress, stabilizes the microstructure and mechanical properties, and ensures that neodymium is uniformly dispersed in the matrix. After annealing, the forging undergoes surface finishing and non-destructive testing to ensure the absence of defects such as cracks, inclusions, and porosity, ultimately yielding a finished TC6 titanium alloy forging for aerospace applications.

[0017] The present solution will be further explained below with reference to the embodiments and comparative examples.

[0018] Example 1 (1) TC6 titanium alloy ingots were prepared by three-stage vacuum arc remelting (VAR), with an ingot diameter of Φ500mm and a length of 1200mm. At the end of the third VAR remelting, 0.12wt% Nd was added in the form of an Al-Nd master alloy and stirred thoroughly for 30min using an electromagnetic stirring device to ensure that the Nd element was uniformly melted into the ingot matrix. The ingot billet was surface-polished and refinished to remove surface oxide scale, cracks and other defects, so that the surface finish of the billet reached Ra1.2μm. Subsequently, a 0.2mm thick Al2O3-SiO2 ceramic high-temperature protective coating was applied to the surface of the billet by spraying and dried for later use. The coated billet was placed in a resistance heating furnace, heated to 900℃, held for 18h, and after the holding period, the furnace was cooled to below 500℃ and then air-cooled to room temperature.

[0019] (2) The β-phase transformation temperature T of this batch of TC6 titanium alloy was tested. β The temperature is 990℃; the pretreated billet is placed in a resistance heating furnace and heated to T at a heating rate of 8℃ / min. β +130℃ (i.e., 1120℃), because the billet cross-sectional diameter is 500mm (greater than 300mm), hold for 6 hours to ensure full firing and uniform Nd element distribution. After holding, quickly remove from the furnace, use a forging hammer to chamfer and upset the four corners of the billet, and then use a combination of upsetting and drawing forging to perform two-pass forging to square the billet; the deformation per pass in each pass is 35%, the cumulative deformation is 68%, and the forging ratio is 1.7; the first pass uses radial drawing, and the second pass uses axial drawing, with an axial drawing feed of 250mm and a drawing rate of 60mm / s; the upsetting process uses slow split hammer upsetting at an upsetting rate of 15mm / s. After each forging pass, forced air cooling is used. Because the equivalent diameter of the forging cross-section is greater than 300mm, staged cooling is used: first, forced air cooling at a cooling rate of 4℃ / s to 600℃, and then air cooling to room temperature.

[0020] (3) Using the sub-β forging mode, the billet after the initial forging is heated to T. β -50℃ (i.e. 940℃), heat preservation for 8 hours, forging ratio 1.4, using flat square drawing process; drawing feed amount 280mm, drawing rate 60mm / s, single-pass deformation amount 35%, cumulative deformation amount 68%, the cross section of the forged billet is square (side length 320mm), and air-cooled to room temperature after forging.

[0021] (4) The billet after secondary forging is heated to 940℃ and held for 6 hours to ensure uniform temperature and full utilization of Nd. After holding, it is taken out of the furnace and forged in one pass using direct drawing forging; the deformation per pass is 18%, the drawing feed is 220mm, and the drawing rate is 60mm / s. During the final forging process, the billet temperature is monitored in real time. When the billet temperature is lower than 850℃, it is returned to the furnace to be heated to 940℃, heated once, and held for 1.2 hours; after heating, the final forging is continued. After the final forging is completed, it is air-cooled to room temperature to obtain TC6 titanium alloy forging billet.

[0022] (5) The forging blank is subjected to isothermal annealing. The annealing process is as follows: hold at 860℃ for 1.5h, then furnace cool to 650℃ and hold for 2h, and then air cool to room temperature. After annealing, the surface of the forging is finely repaired to remove the surface oxide layer and forging marks. Then, ultrasonic testing and penetrant testing are used for non-destructive testing to ensure that the forging is free from defects such as cracks, inclusions, and porosity. Finally, the finished TC6 titanium alloy forging for aviation (size: 320mm×320mm×800mm) is obtained.

[0023] Example 2 (1) TC6 titanium alloy ingots were prepared by three-stage vacuum arc remelting (VAR), with an ingot diameter of Φ500mm and a length of 1200mm. At the end of the third VAR remelting, 0.12wt% Nd was added in the form of an Al-Nd master alloy and stirred thoroughly for 30min using an electromagnetic stirring device to ensure that the Nd element was uniformly melted into the ingot matrix. The ingot billet was surface-polished and refinished to remove surface oxide scale, cracks and other defects, so that the surface finish of the billet reached Ra1.2μm. Subsequently, a 0.2mm thick Al2O3-SiO2 ceramic high-temperature protective coating was applied to the surface of the billet by spraying and dried for later use. The coated billet was placed in a resistance heating furnace, heated to 900℃, held for 18h, and after the holding period, the furnace was cooled to below 500℃ and then air-cooled to room temperature.

[0024] (2) The β-phase transformation temperature T of this batch of TC6 titanium alloy was tested. β The temperature is 990℃; the pretreated billet is placed in a resistance heating furnace and heated to T at a heating rate of 8℃ / min. β+130℃ (i.e., 1120℃), because the billet cross-sectional diameter is 500mm (greater than 300mm), hold for 6 hours to ensure full firing and uniform Nd element distribution. After holding, quickly remove from the furnace, use a forging hammer to chamfer and upset the four corners of the billet, and then use a combination of upsetting and drawing forging to perform two-pass forging to square the billet; the deformation per pass in each pass is 35%, the cumulative deformation is 68%, and the forging ratio is 1.7; the first pass uses radial drawing, and the second pass uses axial drawing, with an axial drawing feed of 250mm and a drawing rate of 60mm / s; the upsetting process uses slow split hammer upsetting at an upsetting rate of 15mm / s. After each forging pass, forced air cooling is used. Because the equivalent diameter of the forging cross-section is greater than 300mm, staged cooling is used: first, forced air cooling at a cooling rate of 4℃ / s to 600℃, and then air cooling to room temperature.

[0025] (3) The super β forging mode is adopted. The billet after the blanking is heated to 1030℃ and held for 5h. The forging ratio is 1.6 and the diagonal drawing process is adopted. The drawing feed is 280mm, the drawing rate is 60mm / s, the single-pass deformation is 35%, the cumulative deformation is 68%, and the cross section of the forged billet is square (side length 320mm). After forging, the blank is air-cooled to room temperature. The Nd element effectively inhibits the abnormal precipitation and growth of the α phase and ensures the uniformity of the forging structure.

[0026] (4) The billet after secondary forging is heated to 940℃ and held for 6 hours to ensure uniform temperature and full utilization of Nd. After holding, it is taken out of the furnace and forged in one pass using direct drawing forging; the deformation per pass is 18%, the drawing feed is 220mm, and the drawing rate is 60mm / s. During the final forging process, the billet temperature is monitored in real time. When the billet temperature is lower than 850℃, it is returned to the furnace to be heated to 940℃, heated once, and held for 1.2 hours; after heating, the final forging is continued. After the final forging is completed, it is air-cooled to room temperature to obtain TC6 titanium alloy forging billet.

[0027] (5) The forging blank is subjected to isothermal annealing. The annealing process is as follows: hold at 860℃ for 1.5h, then furnace cool to 650℃ and hold for 2h, and then air cool to room temperature. After annealing, the surface of the forging is finely repaired to remove the surface oxide layer and forging marks. Then, ultrasonic testing and penetrant testing are used for non-destructive testing to ensure that the forging is free from defects such as cracks, inclusions, and porosity. Finally, the finished TC6 titanium alloy forging for aviation (size: 320mm×320mm×800mm) is obtained.

[0028] Comparative Example 1 Using the exact same process route and parameters as in Example 1, except that Nd was not added during the three vacuum arc melting processes, all other operations were the same, to prepare conventional TC6 titanium alloy forgings.

[0029] The forgings prepared in Examples 1, 2, and Comparative Example 1 were tested for room temperature mechanical properties and high temperature creep properties. The test results are shown in the table below:

[0030] As can be seen from the table above, the forgings prepared in Examples 1 and 2 are superior to the forgings prepared in Comparative Example 1 in terms of tensile strength, yield strength, elongation, reduction of area, and creep rupture time at 600℃ / 100MPa.

Claims

1. A forging method for TC6 titanium alloy for aerospace applications, characterized in that, Includes the following steps: a. Pretreatment of ingot billets: TC6 titanium alloy ingots were prepared by three-stage vacuum arc melting. At the end of the third vacuum arc melting, neodymium was added as a microalloying element in the form of Al-Nd master alloy at a mass percentage of 0.08% to 0.15%. The added neodymium was stirred to ensure uniform melting, and ingot billet was obtained. The surface of the ingot blank is ground to achieve a surface finish of ≤Ra1.6 μm, and then a ceramic high-temperature protective coating with a thickness of 0.1 mm to 0.3 mm is applied to the surface of the ingot blank. The ingot billet is placed in a resistance heating furnace and held at 880 ℃ to 920 ℃ for 12 h to 24 h. After the holding period, the furnace is cooled to below 500 ℃ and then air-cooled to room temperature. b. Place the pretreated ingot billet in a resistance heating furnace and heat it to T at a heating rate of 5℃ / min to 10℃ / min. β +(100~160) ℃; When the cross-sectional diameter of the ingot billet is less than 300 mm, the holding time is 3 to 5 hours. When the cross-sectional diameter of the ingot billet is greater than 300 mm, it should be kept at a temperature of 5 to 7 hours. After the heat preservation is completed, the ingot billet is taken out of the furnace. First, the edges and corners of the ingot billet are chamfered and upset flat. Then, it is forged by upset drawing combination forging for 1 to 3 times to draw and square the billet. The deformation amount per pass is 30% to 40%, the cumulative deformation amount is ≥60%, and the forging ratio is 1.4 to 2.

0. Within the same firing cycle, the first drawing is radial drawing, and the second drawing is axial drawing. The axial drawing feed is 200 mm to 300 mm, and the drawing rate is 40 mm / s to 80 mm / s. The upsetting is slow hammer upsetting, and the upsetting rate is 10 mm / s to 20 mm / s. Forced air cooling is used after each forging cycle. When the equivalent diameter of the forging section is ≤300mm, a cooling rate of 2℃ / s to 5℃ / s is adopted; when the equivalent diameter of the forging section is greater than 300mm, staged cooling is adopted. c. Forging is carried out using sub-β forging or super-β forging. During the forging process, the drawing feed is 250 mm to 300 mm, the drawing rate is 40 mm / s to 80 mm / s, the deformation per pass is 25% to 45%, the cumulative deformation is ≥65%, the cross section of the forged billet is square, and the billet is air-cooled to room temperature after each forging. d. Heat the billet obtained from forging in step c to T. β -(30~70) ℃, keep warm for 5 to 7 hours to ensure uniform temperature; After heat preservation, the product is taken out of the furnace and then forged in one pass using straight drawing forging. The deformation amount of the single pass of the final forging is 12% to 25%, the drawing feed is 200mm to 250mm, and the drawing rate is 40mm / s to 80mm / s. During the final forging process, when the billet temperature is below 850 ℃, it is returned to the furnace for reheating to the set final forging temperature. The number of reheating times during the entire final forging process is ≤2 times, and each reheating is held for 1 h to 1.5 h. If the number of heating cycles exceeds 2 or a single heating cycle exceeds the time limit, the billet should be re-evaluated or scrapped. After final forging, the blank is air-cooled to room temperature to obtain a TC6 titanium alloy forging. e. The forging blank is isothermally annealed, then furnace cooled to 650 ℃ and held for 2 h, followed by air cooling to room temperature; After air cooling to room temperature, the forgings undergo surface finishing and non-destructive testing to ensure the absence of cracks, inclusions, and porosity, ultimately yielding finished TC6 titanium alloy forgings for aerospace applications.

2. The forging method of TC6 titanium alloy for aerospace applications as described in claim 1, characterized in that: For forgings with an equivalent cross-sectional diameter greater than 300 mm, the staged cooling process is as follows: first, strong air cooling at 3℃ / s to 5℃ / s to approximately 600℃, followed by air cooling to room temperature.

3. The forging method of TC6 titanium alloy for aerospace applications as described in claim 1 or 2, characterized in that: In step c, the sub-β forging method is: heating to T β -(40~60)℃, heat preservation for 7 h to 9 h, forging ratio 1.2 to 1.6, using flat square drawing.

4. The forging method of TC6 titanium alloy for aerospace applications as described in claim 1 or 2, characterized in that: In step c, the super β forging method is as follows: heating to T β +(20~60) ℃, heat treatment for 4 h to 6 h, forging ratio 1.4 to 1.8, and diagonal drawing.

5. The forging method of TC6 titanium alloy for aerospace applications as described in claim 1 or 2, characterized in that: In step e, the forging blank is annealed isothermally at 860 ℃ for 1.5 h.

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