Titanium alloy material heat treatment method for aircraft

Abstract

The application discloses a heat treatment method of a titanium alloy material for an aviation aircraft, and comprises the following steps: S1, heating forging; S2, die forging; and S3, double annealing heat treatment. The heat treatment method optimizes and adjusts the heat treatment process in the preparation process of the TC21 titanium alloy, mainly optimizes and adjusts the cooling mode, the holding time and other parameters of the double annealing, so that the cooling speed is adjusted, the secondary lamellar or spherical alpha phase is obtained in the first annealing, the acicular alpha phase is obtained in the second annealing, the strength of the titanium alloy is improved through the content of the alpha phase, and the prepared TC21 titanium alloy meets the high performance requirements of strength greater than or equal to 1200 MPa, yield greater than or equal to 1100 MPa and A greater than or equal to 8.

Description

TECHNICAL FIELD

[0001] The application relates to an aviation material preparation and processing technology field, in particular to a heat treatment method of a titanium alloy material for an aviation aircraft. BACKGROUND

[0002] TC21 titanium alloy is a new type of high-strength high-toughness damage tolerance titanium alloy developed by China, various mechanical properties of which are stable, and the TC21 titanium alloy has good matching of strength, plasticity, fracture toughness and crack propagation rate, and is a high-strength high-toughness damage tolerance structural titanium alloy with very promising application prospect. With the rapid development of the aviation industry towards structural lightweight, the emergence of new alloy materials is undoubtedly an important symbol of the development of advanced aircraft in China. In order to accelerate the application of the TC21 titanium alloy in the aviation industry, the related theory needs to be researched, a mature processing technology needs to be formed, and the performance potential needs to be developed, so that the TC21 titanium alloy can meet the performance requirements of the aviation industry on structural materials.

[0003] The TC21 titanium alloy belongs to a two-phase titanium alloy, and typical microstructures mainly include four types of equiaxed structure, duplex structure, basketweave structure and widmanstatten structure. The basketweave structure is a structure woven into a basketweave structure by transformed alpha phase, the basketweave structure has high strength and fracture toughness, and has strong crack propagation resistance, and is an ideal structure of a part serving at high temperature for a long time.

[0004] In order to obtain the structure, in addition to controlling the hot working process, the heat treatment system needs to be adjusted, so that the TC21 titanium alloy can meet the high-performance requirements of strength being greater than or equal to 1200MPa, yield being greater than or equal to 1100MPa, and A being greater than or equal to 8. SUMMARY

[0005] In view of the above problems, the application provides a heat treatment method of a titanium alloy material for an aviation aircraft.

[0006] The technical scheme of the application is as follows:

[0007] A heat treatment method of a titanium alloy material for an aviation aircraft, comprising the following steps:

[0008] S1, heating forging: after TC21 titanium alloy blank is loaded into a furnace, heating forging is performed, the heating forging temperature is T β -35℃, the holding time is 120-150min, after the heating forging is completed, the furnace is discharged and air cooling is performed until room temperature is reached, and a forged piece blank is obtained;

[0009] S2, die forging: the surface of the forged piece blank is cleaned, then the forged piece blank is loaded into the furnace and held at 120-150℃ for 10-20min, after being taken out, glass lubricant is sprayed on the surface of the forged piece blank, then the forged piece blank is loaded into the furnace again and heated, the heating forging temperature is T β- 35℃, the holding time is 180-200 min, the forging blank is taken out and transferred to the die for forging forming, and a die forging part is obtained;

[0010] S3, double annealing heat treatment: the die forging part obtained in step S2 is loaded into the furnace and annealed at 890±10℃ for 120±5 min, and then air-cooled to room temperature. Subsequently, the die forging part obtained after the first annealing is loaded into the furnace and annealed at 510±10℃ for 240±5 min, and then air-cooled to room temperature, thereby obtaining a TC21 titanium alloy part.

[0011] Further, the die forging part obtained in step S2 is taken out and air-cooled to room temperature, and then cut into a plurality of cuboid test rod blanks, the size of the test rod blank being: length 15-30 mm, width 15-30 mm, and height 75-120 mm.

[0012] Then, double annealing heat treatment is performed: the obtained test rod blank is loaded into the furnace and annealed at 890±10℃ for 120±5 min, and then air-cooled to room temperature. Subsequently, the test rod blank obtained after the first annealing is loaded into the furnace and annealed at 510±10℃ for 240±5 min, and then air-cooled to room temperature, thereby obtaining a TC21 titanium alloy part.

[0013] Description: By cutting the entire die forging part into a plurality of test rod blanks, and then adjusting and optimizing the size of the test rod blank, the performance of the TC21 titanium alloy is further improved. The TC21 titanium alloy part obtained after the double annealing heat treatment of the test rod blank with a smaller size has a higher elongation, and the tensile strength and yield strength meet the requirements. The TC21 titanium alloy part obtained after the double annealing heat treatment of the die forging part has a higher tensile strength and yield strength, and the elongation also meets the requirements. The selection can be made according to the needs.

[0014] Further, the T β is the β transformation temperature of the TC21 titanium alloy, and is 950-990℃.

[0015] Description: The temperature during heating forging and die forging is controlled based on the β transformation temperature of the TC21 titanium alloy, that is, the lowest temperature at which the TC21 titanium alloy is completely transformed into a β phase structure during the heating process, so that the heating temperature is always controlled below the β phase transformation point according to the individual differences of the material.

[0016] Further, in step S2, the time for transferring the forging blank to the die after taking it out is ≤15 s, and the final forging temperature of the forging blank in the die is not lower than 800℃ and not higher than 900℃.

[0017] Description: By strictly controlling the time of taking out the forging blank and transferring it into the die to ensure the size of the final forging temperature, thereby ensuring the performance of the TC21 titanium alloy.

[0018] Further, in steps S1 and S3, the room temperature is 24-30 DEG C.

[0019] Further, in step S2, the surface of the forging blank is cleaned by sandblasting to remove dirt and grease on the surface of the forging blank.

[0020] Further, in step S2, the die forging obtained is a cylinder with an upper end diameter of 90-100 mm, a lower end diameter of 150-160 mm and a height of 200-400 mm.

[0021] Further, in step S3, the gas used for air cooling is argon, the air cooling is carried out at a cooling air speed of 2-5 m / s.

[0022] Description: By controlling the conditions of air cooling, the cooling of the test bar blank is accelerated.

[0023] Further, when the test bar blanks are loaded into the furnace, 12-25 test bar blanks are laid on each layer of the furnace at equal intervals, and the distance between two adjacent test bar blanks is 50-60 mm.

[0024] Description: By the heating arrangement method, the test bar blanks are heated more uniformly.

[0025] Further, in step S3, the surface impurities of the die forging are removed by cleaning before the first annealing treatment.

[0026] The present application has the following beneficial effects:

[0027] (1) The heat treatment method of the present application optimizes and adjusts the heat treatment process in the preparation process of the TC21 titanium alloy, mainly optimizes and adjusts the cooling mode, holding time and other parameters of the double annealing, so as to achieve the purpose of adjusting the cooling speed, and then obtain secondary lamellar or spherical alpha phase in the first annealing, and obtain needle-like alpha phase in the second annealing, and the content of alpha phase is improved to improve the strength of the titanium alloy, so that the prepared TC21 titanium alloy meets the high performance requirements of strength ≥ 1200 MPa, yield ≥ 1100 MPa and A ≥ 8.

[0028] (2) The heat treatment method of the application further improves the performance of the TC21 titanium alloy by sawing the entire die forging into a plurality of test bar blanks, and then adjusting and optimizing the size of the test bar blanks, so that the TC21 titanium alloy parts obtained by double annealing heat treatment of the test bar blanks with smaller size have higher elongation, while the tensile strength and yield strength meet the requirements, and the TC21 titanium alloy parts obtained by directly double annealing heat treatment of the die forgings have higher tensile strength and yield strength, while the elongation also meets the requirements, which can be selected according to needs.

[0029] (3) The heat treatment method of the application controls the temperature during heating forging and die forging by the beta transformation temperature of the TC21 titanium alloy, that is, the lowest temperature at which the TC21 titanium alloy is completely transformed into beta phase structure during heating, so that the heating temperature is always controlled below the beta phase transition point according to the individual differences of the material, and the size of the final forging temperature is ensured by strictly controlling the time of the forging blank after being removed from the die, thereby ensuring the performance of the TC21 titanium alloy. BRIEF DESCRIPTION OF DRAWINGS

[0030] Figure 1 is a flow chart of a heat treatment method of a titanium alloy material for an aircraft of the application. DETAILED DESCRIPTION

[0031] Example 1

[0032] S1, heating forging: after the TC21 titanium alloy blank is loaded into the furnace, heating forging is carried out, the heating forging temperature is T β -35℃, the holding time is 130min, after the heating forging is completed, the furnace is discharged and air cooled to room temperature, a forging blank is obtained, and the forging furnace is a class II electric furnace;

[0033] S2, die forging: the surface of the forging blank is cleaned, the surface cleaning method is sandblasting, which removes dirt and grease on the surface of the forging blank, then the forging blank is loaded into the furnace and held at 135℃ for 15min, the forging blank is taken out and sprayed with glass lubricant on the surface, then the forging blank is reloaded into the furnace for heating forging, the heating forging temperature is T β -35℃, the holding time is 190min, the forging blank is taken out and transferred to the die for forging, the time for transferring the forging blank to the die is 8s, and the final forging temperature of the forging blank in the die is 830℃, obtaining a die forging;

[0034] The above T βThe beta transus temperature of the TC21 titanium alloy, the alpha type, the alpha-beta type and the metastable beta type alloy contain a certain amount of primary alpha phase or aging precipitation alpha phase after smelting, hot deformation, annealing and aging. With the increase of temperature, the alpha phase in the titanium alloy gradually decreases, and all the beta phase organization is obtained after a certain critical temperature is reached and rapid quenching is carried out after a certain time is kept at the critical temperature; the beta transus temperature T β of the titanium alloy is determined by observing the metallographic structure of the sample after quenching treatment at different temperatures according to the preset temperature interval. β According to the GB / T23605-2020 standard, the T β of the TC21 titanium alloy is 950-990℃, and in actual operation, the corresponding T β is selected according to the individual differences of the TC21 titanium alloy, and the measured T β of the same batch of materials selected here is 960℃.

[0035] S3, double annealing heat treatment: the die forging obtained in step S2 is loaded into the furnace and annealed at 890℃ for 120min, and then air-cooled to room temperature, and then the die forging obtained by the first annealing is loaded into the furnace and annealed at 510℃ for 240min, and then air-cooled to room temperature, to obtain the TC21 titanium alloy part, and the room temperature in steps S1 and S3 is 25℃.

[0036] Example 2

[0037] The difference between this embodiment and example 1 is that the specific parameters are different.

[0038] S1, heating forging: the TC21 titanium alloy blank is loaded into the furnace and heated to a temperature of T β -35℃, and the holding time is 120min, and then the furnace is discharged and air-cooled to room temperature to obtain a forging blank;

[0039] S2, die forging: the surface of the forging blank is cleaned, the surface cleaning method is sandblasting, and the surface dirt and grease of the forging blank is removed, then the furnace is loaded and annealed at 120℃ for 10min, then the forging blank is taken out and sprayed with glass lubricant on the surface, then the forging blank is reheated and forged in the furnace, the temperature of the heating forging is T β -35℃, the holding time is 180min, the forging blank is taken out and transferred to the die for forging, the time for transferring the forging blank to the die is 10s, and the final forging temperature of the forging blank in the die is 810℃, to obtain a die forging;

[0040] The measured T β of the same batch of materials selected here is 950℃.

[0041] S3, double annealing heat treatment: before the first annealing treatment, the surface impurities of the die forging are cleaned and removed, the die forging obtained in step S2 is loaded into the furnace and annealed at 880 ℃ for 115 min, the first annealing treatment is carried out, and after being taken out of the furnace, air cooling is performed to room temperature, the gas used for air cooling is argon, the air cooling chamber is filled with argon at a pressure of 1.9 bar, the cooling air speed during air cooling is 2 m / s, and then the die forging obtained after the first annealing treatment is loaded into the furnace and annealed at 500 ℃ for 235 min, the second annealing treatment is carried out, and after being taken out of the furnace, air cooling is performed to room temperature, thereby obtaining a TC21 titanium alloy part, and the room temperature in steps S1 and S3 is 24℃.

[0042] Example 3

[0043] The difference between this example and example 1 is that the specific parameters are different.

[0044] S1, heating forging: the TC21 titanium alloy blank is loaded into the furnace and heated and forged, the heating forging temperature is T β -35℃, the holding time is 150 min, after the heating forging is completed, the blank is taken out of the furnace and air cooled to room temperature, thereby obtaining a blank;

[0045] S2, die forging: the surface of the blank is cleaned, the surface cleaning method is sandblasting, and the surface dirt and grease of the blank are removed, then the blank is loaded into the furnace and annealed at 150℃ for 20 min, and then the blank is taken out and glass lubricant is sprayed on the surface of the blank, then the blank is loaded into the furnace again and heated and forged, the heating forging temperature is T β -35℃, the holding time is 200 min, the blank is taken out of the furnace and transferred to the die for forging, the time for transferring the blank to the die is 15 s, and the final forging temperature of the blank in the die is 850℃, thereby obtaining a die forging;

[0046] Here, the measured T β of the same batch of materials is 990℃;

[0047] S3, double annealing heat treatment: before the first annealing treatment, the surface impurities of the die forging are cleaned and removed, the die forging obtained in step S2 is loaded into the furnace and annealed at 900 ℃ for 125 min, the first annealing treatment is carried out, and after being taken out of the furnace, air cooling is performed to room temperature, the gas used for air cooling is argon, the air cooling chamber is filled with argon at a pressure of 2 bar, the cooling air speed during air cooling is 5 m / s, and then the die forging obtained after the first annealing treatment is loaded into the furnace and annealed at 520 ℃ for 245 min, the second annealing treatment is carried out, and after being taken out of the furnace, air cooling is performed to room temperature, thereby obtaining a TC21 titanium alloy part, and the room temperature in steps S1 and S3 is 30℃.

[0048] Example 4

[0049] The difference between this example and example 1 is that

[0050] After the die forging is taken out and air-cooled to room temperature, the die forging is a cylinder with an upper end diameter of 95 mm, a lower end diameter of 155 mm and a height of 300 mm, and then the die forging is sawn into a plurality of cuboid test bar blanks, the size of the test bar blank being 20 mm in length, 20 mm in width and 90 mm in height;

[0051] Then, double annealing heat treatment is carried out: before the first annealing treatment, the surface impurities of the test bar blank are cleaned and removed, the test bar blank is loaded into the furnace, and then heat preservation is carried out at 890 ℃ for 120 min, the first annealing treatment is carried out, air cooling is carried out to room temperature after the furnace is discharged, argon gas is used for air cooling, the gas filling pressure of the cooling chamber is 1.95 bar, the cooling air speed during air cooling is 3 m / s, then the test bar blank obtained after the first annealing treatment is loaded into the furnace, and then heat preservation is carried out at 510 ℃ for 240 min, the second annealing treatment is carried out, air cooling is carried out to room temperature after the furnace is discharged, a TC21 titanium alloy part is obtained, the room temperature is 26 ℃, 20 test bar blanks are laid in each layer at equal intervals in the furnace when the test bar blank is loaded into the furnace, the distance between adjacent two test bar blanks is 55 mm, and the heat treatment furnace is a class III electric furnace.

[0052] Example 5

[0053] The difference between this embodiment and example 2 is that:

[0054] After the die forging is taken out and air-cooled to room temperature, the die forging is a cylinder with an upper end diameter of 95 mm, a lower end diameter of 155 mm and a height of 300 mm, and then the die forging is sawn into a plurality of cuboid test bar blanks, the size of the test bar blank being 20 mm in length, 20 mm in width and 90 mm in height;

[0055] Then, double annealing heat treatment is carried out: before the first annealing treatment, the surface impurities of the test bar blank are cleaned and removed, the test bar blank is loaded into the furnace, and then heat preservation is carried out at 890 ℃ for 120 min, the first annealing treatment is carried out, air cooling is carried out to room temperature after the furnace is discharged, argon gas is used for air cooling, the gas filling pressure of the cooling chamber is 1.95 bar, the cooling air speed during air cooling is 3 m / s, then the test bar blank obtained after the first annealing treatment is loaded into the furnace, and then heat preservation is carried out at 510 ℃ for 240 min, the second annealing treatment is carried out, air cooling is carried out to room temperature after the furnace is discharged, a TC21 titanium alloy part is obtained, the room temperature is 26 ℃, 20 test bar blanks are laid in each layer at equal intervals in the furnace when the test bar blank is loaded into the furnace, the distance between adjacent two test bar blanks is 55 mm, and the heat treatment furnace is a class III electric furnace.

[0056] Example 6

[0057] The difference between this embodiment and example 3 is that:

[0058] After the die forging is taken out and air-cooled to room temperature, the die forging is a cylinder with an upper end diameter of 100 mm, a lower end diameter of 160 mm and a height of 400 mm, and then the die forging is sawn into a plurality of cuboid test bar blanks, and the size of the test bar blank is 30 mm in length, 30 mm in width and 120 mm in height;

[0059] Then, double annealing heat treatment is performed: before the first annealing treatment, the surface impurities of the test bar blank are cleaned and removed, the test bar blank is loaded into the furnace, and then annealing treatment is performed at 900 DEG C for 125 min, and then air-cooled to room temperature after being taken out of the furnace, the gas used for air-cooling is argon, the gas filling pressure of the cooling chamber is 2 bar, the cooling air speed during air-cooling is 5 m / s, and then the test bar blank after the first annealing treatment is loaded into the furnace and then annealing treatment is performed at 520 DEG C for 245 min, and then air-cooled to room temperature after being taken out of the furnace, thereby obtaining a TC21 titanium alloy part, the room temperature is 30 DEG C, and when the test bar blank is loaded into the furnace, 25 test bar blanks are laid in each layer at equal intervals in the furnace, and the distance between adjacent two test bar blanks is 60 mm.

[0060] Experimental example

[0061] The method in examples 1-6 is used to perform on-site preparation test and test the performance of the product, and a plurality of comparative examples are set to perform comparison, wherein, the comparative example 1 is basically the same as the example 1, except that the heating temperature of the first annealing is 900 DEG C, the holding time is 150 min, the cooling mode is air-cooling, the heating temperature of the second annealing is 590 DEG C, the holding time is 240 min, and the cooling mode is air-cooling.

[0062] The comparative example 2 is basically the same as the example 1, except that the heating temperature of the first annealing is 900 DEG C, the holding time is 150 min, the cooling mode is water-cooling, the water temperature is 95 DEG C, the heating temperature of the second annealing is 590 DEG C, the holding time is 240 min, and the cooling mode is air-cooling.

[0063] The comparative example 3 is basically the same as the example 1, except that the heating temperature of the first annealing is 890 DEG C, the holding time is 180 min, the cooling mode is air-cooling, the heating temperature of the second annealing is 510 DEG C, the holding time is 240 min, and the cooling mode is air-cooling.

[0064] The comparative example 4 is basically the same as the example 1, except that the heating temperature of the first annealing is 900 DEG C, the holding time is 120 min, the cooling mode is oil-cooling, the oil temperature is 45 DEG C, the heating temperature of the second annealing is 590 DEG C, the holding time is 240 min, and the cooling mode is air-cooling.

[0065] Comparative Example 5 is basically the same as Example 1, except that the heating temperature of the first annealing is 890℃, the holding time is 120min, the cooling method is water cooling with water temperature of 95℃, the heating temperature of the second annealing is 590℃, the holding time is 240min, and the cooling method is air cooling;

[0066] The properties of the TC21 titanium alloy parts prepared in Examples 1, 4-6 and Comparative Examples 1-5 were then detected, and the results are shown in Table 1. It should be noted that in Examples 1-6, the parameters in steps S1, S2 and S3 were selected within a reasonable error range and had little effect on the experimental results. However, the adjustment of the parameters for sawing the test bar blanks had an effect on the experimental results. This is because smaller test bar blanks are quenched faster during cooling, and thus the α phase content is different, thereby affecting the final properties of the TC21 titanium alloy parts.

[0067] Table 1 Properties of TC21 titanium alloy parts of examples and comparative examples

[0068]

[0069] As can be seen from the data in Table 1, the TC21 titanium alloy parts prepared in Examples 1, 4-6 meet the high performance requirements of strength ≥ 1200MPa, yield ≥ 1100MPa, and A ≥ 8, and meet the requirements of aircraft material properties. This is because in the examples and comparative examples, we mainly adjusted the cooling method and holding time of the double annealing heat treatment. Different cooling methods result in different cooling rates, and the cooling rate of TC21 titanium alloy is water cooling > oil cooling > air cooling > air cooling. Therefore, it can be seen that in Comparative Examples 2, 4 and 5, the faster cooling method is used, thereby increasing the tensile strength and yield strength of the TC21 titanium alloy parts, but greatly reducing the elongation after fracture. The secondary lamellar or spherical α phase is obtained by the first annealing, and the acicular α phase is obtained by the second annealing. The content of α phase improves the strength of the titanium alloy, but too much α phase also affects the plasticity of the material, greatly reducing the elongation after fracture;

[0070] By comparing the two sets of data in Example 1 and Example 4, it can be seen that the TC21 titanium alloy parts obtained by double annealing heat treatment of test bar blanks with smaller sizes have higher elongation, and the tensile strength and yield strength meet the requirements. However, the TC21 titanium alloy parts obtained by directly double annealing heat treatment of the die forgings have higher tensile strength and yield strength, and the elongation also meets the requirements. The selection can be made according to the needs.

[0071] In Comparative Example 1, the main difference from the examples is that the heating temperature of the second annealing is higher, and the tensile strength and yield strength of the TC21 titanium alloy parts obtained are lower.

[0072] In Comparative Example 3, the main difference from the examples is that the holding time during the first annealing is longer, thus resulting in a decrease in the tensile strength and yield strength of the TC21 titanium alloy part;

[0073] In comparison of the examples in each group, it can be seen that the TC21 titanium alloy part prepared in Example 1 has the best performance.

Claims

1. A heat treatment method of a titanium alloy material for an aircraft, characterized by, The method comprises the following steps: S1, heating forging: after the TC21 titanium alloy blank is loaded into the furnace, heating forging is performed, the temperature of the heating forging is T β -35℃, the holding time is 120-150 min, after the heating forging is completed, the furnace is discharged and air cooling is performed, and the forging blank is obtained after cooling to room temperature; S2, die forging: the surface of the forging blank is cleaned, then it is put into the furnace for heat preservation at 120-150°C for 10-20 min, after taking out, the glass lubricant is sprayed on the surface of the forging blank, then the forging blank is put into the furnace again for heating and forging, the heating and forging temperature is T β -35°C, the heat preservation time is 180-200 min, the forging blank is taken out and transferred into the die for forging and forming to obtain a die forging, the die forging obtained in step S2 is taken out and air cooled to room temperature, then the die forging is sawn into a plurality of cuboid test bar blank pieces, the size of the test bar blank piece is: length 15-30 mm, width 15-30 mm, height 75-120 mm; S3, double annealing heat treatment: the test bar blank obtained in step S2 is put into the furnace and kept at 890±10℃ for 120±5min for primary annealing treatment, and then air-cooled to room temperature, and then the test bar blank after the primary annealing treatment is put into the furnace and kept at 510±10℃ for 240±5min for secondary annealing treatment, and then air-cooled to room temperature to obtain the TC21 titanium alloy part.

2. The heat treatment method of a titanium alloy material for an aircraft according to claim 1, characterized by, The T β The β transus temperature for TC21 titanium alloy is 950-990°C.

3. The heat treatment method of titanium alloy material for an aircraft according to claim 1, characterized in that, In step S2, the time for taking out the forging blank and transferring it into the die is ≤15s, and the final forging temperature of the forging blank in the die is not lower than 800℃ and not higher than 900℃.

4. The heat treatment method of titanium alloy material for an aircraft according to claim 1, characterized in that, In steps S1 and S3, the room temperature is 24-30℃.

5. The heat treatment method of titanium alloy material for an aircraft according to claim 1, characterized in that, In step S2, the surface of the forging blank is cleaned by sandblasting to remove dirt and grease on the surface of the forging blank.

6. The heat treatment method of titanium alloy material for an aircraft according to claim 1, characterized in that, In step S2, the obtained die forging part is a cylinder with an upper end diameter of 90-100mm, a lower end diameter of 150-160mm and a height of 200-400mm.

7. The method of heat treatment of titanium alloy material for an aircraft according to claim 1, wherein In step S3, the air used for air cooling is argon, the air cooling speed is 2-5m / s, and the air cooling is carried out in a cooling chamber filled with argon at a pressure of 1.9-2bar.

8. The heat treatment method of titanium alloy material for an aircraft according to claim 2, wherein When the test bar blank is put into the furnace, 12-25 test bar blanks are laid on each layer of the furnace at equal intervals, and the distance between two adjacent test bar blanks is 50-60mm.

9. The method of heat treatment of titanium alloy material for an aircraft according to claim 1, wherein In step S3, the surface impurities of the die forging part are removed by cleaning before the primary annealing treatment.

Images