High-temperature alloy material for manufacturing aero-engine fastener and preparation method of high-temperature alloy material

Abstract

The invention relates to the technical field of aviation high-temperature alloy materials and preparation, and discloses a high-temperature alloy material for manufacturing an aero-engine fastener and a preparation method of the high-temperature alloy material for manufacturing the aero-engine fastener, impurities are controlled within a specified range, so that the quality of a forging stock can be ensured during forging of titanium alloy, the purity of the forging stock is improved, and the yield of the titanium alloy is improved. And each step of forging is refined. The high-temperature alloy material for manufacturing the aero-engine fastener and the preparation method thereof are provided. According to the high-temperature alloy material for manufacturing the aero-engine fastener and the preparation method of the high-temperature alloy material, impurities are controlled within a specified range, so that the quality of a forging stock can be guaranteed during forging of titanium alloy, the purity of the forging stock is improved, and the forging quality is improved by refining each step of forging. And through accurate control over the temperature and the time, the forging quality is more accurate, and therefore it can be guaranteed that the needed requirement can be met during forging.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation high-temperature alloy materials and preparation thereof, in particular to high-temperature alloy materials used for manufacturing aviation engine fasteners and a preparation method thereof. Background Art

[0002] As aviation and aerospace vehicles develop towards lightweight, high speed, high reliability and long life, high-performance, high-precision titanium alloy complex thin-walled components are urgently needed. TA15 titanium alloy has high specific strength and high temperature strength at a service temperature of 450-500℃, and its structural benefits are very significant, making TA15 titanium alloy thin-walled components widely needed in aviation, aerospace and other fields.

[0003] Titanium alloy forging is very sensitive to temperature. Currently, there are still deficiencies in temperature control during forging of titanium alloy surfaces. Poor temperature control during forging will lead to reduced metal resistance, which will affect the comprehensive performance of the titanium alloy, and make the titanium alloy grains larger, resulting in a particularly significant reduction in end face shrinkage, which will result in the metal strength failing to meet requirements, leading to unqualified processing. Summary of the invention

[0004] (I) Technical solution

[0005] The present invention provides the following technical solution: a high-temperature alloy material for manufacturing aero-engine fasteners comprises the following raw materials in the following weight proportions: 5-9 parts of aluminum, 1-4 parts of zirconium, 1-5 parts of molybdenum, 1-3 parts of vanadium, and 4-8 parts of thallium.

[0006] Preferably, the impurities are: iron ≤ 0.25%, silicon ≤ 0.15, carbon ≤ 0.10, nitrogen ≤ 0.05, hydrogen ≤ 0.015%, and oxygen ≤ 0.15%.

[0007] A method for preparing a high-temperature alloy material for manufacturing aerospace engine fasteners comprises the following steps:

[0008] S1, blank forging;

[0009] S2, grain refinement treatment;

[0010] S3, intermediate billet forging;

[0011] S4, forming forging.

[0012] Preferably, in step S1, the forging temperature is between 1000 and 1200 degrees, the insulation time is between 240 min and 300 min, the total forging ratio is between 18 and 30, and the obtained billet is first air-cooled and then cooled to room temperature for surface treatment.

[0013] Preferably, in the step S1, the "melting" is performed by fusing and mixing the zero-grade titanium sponge with the internal alloy according to the alloy composition set in advance, creating a vacuum environment, and then melting it by electric arc to obtain an ingot of ta15 titanium alloy.

[0014] Preferably, in step S1, when the β phase region is upset forged, the preliminary forging blank is placed at tβ+60℃~tβ+80℃ for heating and heat preservation, so as to obtain a higher level forging blank, and then the higher level forging blank is placed at tβ+25℃~tβ+30℃ for heating, so as to obtain a secondary forging blank.

[0015] Preferably, in step S2, secondary forging is performed on it by a forging machine of more than 2000t, and the rough wear is heated and kept at 30-70℃ below the phase change point for 300-420min for "refinement treatment". After one forging deformation, it is then heated and kept at 30-50℃ at the phase change point for 210-300min and forged again. The forging ratio is controlled between 12-16 and then air-cooled, and the surface is treated after cooling.

[0016] Preferably, in step S3, the wool pendant is heated and kept at a phase change point of 20-40°C for 240-360 minutes, forged and deformed once, and then heated and kept at a phase change point of 30-50 for 210-300 minutes, the forging ratio is controlled between 12 and 16, and then surface cleaning treatment is performed.

[0017] Preferably, in step S4, the treated forging blank is placed at 30-50°C for heating and insulation, and then deformed by one-fire forging, and then placed at 40-70°C for insulation for 180-240 minutes. After multiple-fire forging times, the total forging ratio is controlled between 3.9 and 5.4, and then air-cooled.

[0018] (II) Beneficial effects

[0019] Compared with the prior art, the present invention provides a high-temperature alloy material for manufacturing aerospace engine fasteners and a preparation method thereof, which has the following beneficial effects:

[0020] 1. The high-temperature alloy material and preparation method for manufacturing aircraft engine fasteners can ensure the quality of the forging blank during forging by controlling impurities within a specified range, thereby improving the purity of the forging blank, and refining each step of forging.

[0021] 2. The high-temperature alloy material and preparation method for manufacturing aircraft engine fasteners make the forging quality more accurate through precise control of temperature and time, thereby ensuring that the required requirements can be met during forging. The hardness is improved by repeatedly forging and controlling the number of forgings to ensure the quality of the forging blank, thereby meeting the set requirements. DETAILED DESCRIPTION

[0022] The following will combine the contents in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] Embodiment 1:

[0024] The present invention provides a technical solution: a high-temperature alloy material for manufacturing aero-engine fasteners comprises the following raw materials in proportion by weight: 5 parts of aluminum, 1 part of zirconium, 1 part of molybdenum, 1 part of vanadium and 4 parts of thallium.

[0025] Impurities: Iron ≤ 0.25%, Silicon ≤ 0.15, Carbon ≤ 0.10, Nitrogen ≤ 0.05, Hydrogen ≤ 0.015%, Oxygen ≤ 0.15%.

[0026] A method for preparing a high-temperature alloy material for manufacturing aerospace engine fasteners comprises the following steps:

[0027] S1, blank forging;

[0028] The forging temperature is at 1000 degrees, the insulation time is 240 minutes, the total forging ratio is 18, the billet is first air-cooled and then at room temperature for surface treatment.

[0029] "Melting" is done by fusing and mixing the zero-grade titanium sponge with the internal alloy according to the pre-set alloy composition, creating a vacuum environment, and then melting it through an electric arc to obtain a TA15 titanium alloy ingot.

[0030] When upsetting and drawing forging is performed in the β phase region, the preliminary forging blank is placed at tβ+60℃ for heating and heat preservation, so as to obtain a higher level forging blank, and then the higher level forging blank is placed at tβ+25℃ for heating, so as to obtain a secondary forging blank.

[0031] S2, grain refinement treatment;

[0032] It is subjected to secondary forging by a forging machine of more than 2000t. For "refine grain treatment", the rough surface is heated and kept at 30℃ below the phase change point for 300min. After one forging deformation, it is heated and kept at 30℃ at the phase change point for 210min and then forged again. The forging ratio is controlled at 12 and then air-cooled. The surface is treated after cooling.

[0033] S3, intermediate billet forging;

[0034] The wool pendant was heated and kept at 20℃, the phase change point, for 240 minutes, and then forged and deformed. Then, the phase change point was heated and kept at 30℃ for 210 minutes. The forging ratio was controlled at 12, and then the surface was cleaned.

[0035] S4, forming forging.

[0036] The treated forging blank is placed at 30℃ for heating and insulation, and then deformed by one-fire forging, and then placed at 40℃ for insulation for 180min. After multiple-fire forging times, the total forging ratio is controlled at 3.9, and then air-cooled.

[0037] Embodiment 2:

[0038] The present invention provides a technical solution: a high-temperature alloy material for manufacturing aero-engine fasteners comprises the following raw materials in proportion by weight: 6 parts of aluminum, 2 parts of zirconium, 3 parts of molybdenum, 2 parts of vanadium and 6 parts of thallium.

[0039] Impurities: Iron ≤ 0.25%, Silicon ≤ 0.15, Carbon ≤ 0.10, Nitrogen ≤ 0.05, Hydrogen ≤ 0.015%, Oxygen ≤ 0.15%.

[0040] A method for preparing a high-temperature alloy material for manufacturing aerospace engine fasteners comprises the following steps:

[0041] S1, blank forging;

[0042] The forging temperature is 1200 degrees, the insulation time is 250 minutes, the total forging ratio is 20, the billet is first air-cooled and then at room temperature for surface treatment.

[0043] "Melting" is done by fusing and mixing the zero-grade titanium sponge with the internal alloy according to the pre-set alloy composition, creating a vacuum environment, and then melting it through an electric arc to obtain a TA15 titanium alloy ingot.

[0044] When upsetting and drawing forging is performed in the β phase region, the preliminary forging blank is placed at tβ+70°C for heating and heat preservation, thereby obtaining a higher level forging blank, and then the higher level forging blank is placed at tβ+27°C for heating, thereby obtaining a secondary forging blank.

[0045] S2, grain refinement treatment;

[0046] It is subjected to secondary forging by a forging machine of more than 2000t. For "refine grain treatment", the rough surface is heated and kept at 35℃ below the phase change point for 340min. After one forging deformation, it is heated and kept at 35℃ at the phase change point for 240min and then forged again. The forging ratio is controlled at 15 and then air-cooled. The surface is treated after cooling.

[0047] S3, intermediate billet forging;

[0048] The wool pendant was placed at a phase change point of 25°C and heated for 260 minutes, and then forged and deformed. Then, the phase change point was heated at 35°C and heated for 240 minutes. The forging ratio was controlled at 14, and then the surface was cleaned.

[0049] S4, forming forging.

[0050] The treated forging billet is heated and kept at 35°C, deformed by one forging, and then kept at 45°C for 200 minutes. After multiple forging times, the total forging ratio is controlled at 5, and then air-cooled.

[0051] Embodiment three:

[0052] The present invention provides a technical solution: a high-temperature alloy material for manufacturing aero-engine fasteners comprises the following raw materials in proportion by weight: 7 parts of aluminum, 4 parts of zirconium, 5 parts of molybdenum, 3 parts of vanadium and 7 parts of thallium.

[0053] Impurities: Iron ≤ 0.25%, Silicon ≤ 0.15, Carbon ≤ 0.10, Nitrogen ≤ 0.05, Hydrogen ≤ 0.015%, Oxygen ≤ 0.15%.

[0054] A method for preparing a high-temperature alloy material for manufacturing aerospace engine fasteners comprises the following steps:

[0055] S1, blank forging;

[0056] The forging temperature is 1200 degrees, the insulation time is 250 minutes, the total forging ratio is 20, the billet is first air-cooled and then at room temperature for surface treatment.

[0057] "Melting" is done by fusing and mixing the zero-grade titanium sponge with the internal alloy according to the pre-set alloy composition, creating a vacuum environment, and then melting it through an electric arc to obtain a TA15 titanium alloy ingot.

[0058] When upsetting and drawing forging is performed in the β phase region, the preliminary forging blank is placed at tβ+70°C for heating and heat preservation, thereby obtaining a higher level forging blank, and then the higher level forging blank is placed at tβ+27°C for heating, thereby obtaining a secondary forging blank.

[0059] S2, grain refinement treatment;

[0060] It is subjected to secondary forging by a forging machine of more than 2000t. For "refine grain treatment", the rough surface is heated and kept at 35℃ below the phase change point for 340min. After one forging deformation, it is heated and kept at 35℃ at the phase change point for 240min and then forged again. The forging ratio is controlled at 15 and then air-cooled. The surface is treated after cooling.

[0061] S3, intermediate billet forging;

[0062] The wool pendant was placed at a phase change point of 25°C and heated for 260 minutes, and then forged and deformed. Then, the phase change point was heated at 35°C and heated for 240 minutes. The forging ratio was controlled at 14, and then the surface was cleaned.

[0063] S4, forming forging.

[0064] The treated forging billet is heated and kept at 35°C, deformed by one forging, and then kept at 45°C for 200 minutes. After multiple forging times, the total forging ratio is controlled at 5, and then air-cooled.

[0065] Embodiment 4:

[0066] The present invention provides a technical solution: a high-temperature alloy material for manufacturing aero-engine fasteners comprises the following raw materials in proportion by weight: 9 parts of aluminum, 4 parts of zirconium, 5 parts of molybdenum, 3 parts of vanadium and 8 parts of thallium.

[0067] Impurities: Iron ≤ 0.25%, Silicon ≤ 0.15, Carbon ≤ 0.10, Nitrogen ≤ 0.05, Hydrogen ≤ 0.015%, Oxygen ≤ 0.15%.

[0068] A method for preparing a high-temperature alloy material for manufacturing aerospace engine fasteners comprises the following steps:

[0069] S1, blank forging;

[0070] The forging temperature is at 1000 degrees, the insulation time is 240 minutes, the total forging ratio is 18, the billet is first air-cooled and then at room temperature for surface treatment.

[0071] "Melting" is done by fusing and mixing the zero-grade titanium sponge with the internal alloy according to the pre-set alloy composition, creating a vacuum environment, and then melting it through an electric arc to obtain a TA15 titanium alloy ingot.

[0072] When upsetting and drawing forging is performed in the β phase region, the preliminary forging blank is placed at tβ+60℃ for heating and heat preservation, so as to obtain a higher level forging blank, and then the higher level forging blank is placed at tβ+25℃ for heating, so as to obtain a secondary forging blank.

[0073] S2, grain refinement treatment;

[0074] It is subjected to secondary forging by a forging machine of more than 2000t. For "refine grain treatment", the rough surface is heated and kept at 30℃ below the phase change point for 300min. After one forging deformation, it is heated and kept at 30℃ at the phase change point for 210min and then forged again. The forging ratio is controlled at 12 and then air-cooled. The surface is treated after cooling.

[0075] S3, intermediate billet forging;

[0076] The wool pendant was heated and kept at 20℃, the phase change point, for 240 minutes, and then forged and deformed. Then, the phase change point was heated and kept at 30℃ for 210 minutes. The forging ratio was controlled at 12, and then the surface was cleaned.

[0077] S4, forming forging.

[0078] The treated forging blank is placed at 30℃ for heating and insulation, and then deformed by one-fire forging, and then placed at 40℃ for insulation for 180min. After multiple-fire forging times, the total forging ratio is controlled at 3.9, and then air-cooled.

[0079] The high-temperature alloy material and preparation method for manufacturing aircraft engine fasteners control impurities within a specified range, so that when forging the titanium alloy, the quality of the forging blank can be guaranteed during forging, thereby improving the purity of the forging blank, and each step of forging is refined and the temperature and time are precisely controlled to make the forging quality more accurate, thereby ensuring that the required requirements can be met during forging, and the hardness is improved on the premise of ensuring the quality of the forging blank through multiple forgings and controlling the number of forgings, thereby meeting the set requirements.

[0080] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. High temperature alloy materials used to manufacture aircraft engine fasteners, It is characterized in that The invention comprises the following raw materials in proportion by weight: 5-9 parts of aluminum, 1-4 parts of zirconium, 1-5 parts of molybdenum, 1-3 parts of vanadium and 4-8 parts of thallium.

2. The high temperature alloy material for manufacturing aerospace engine fasteners according to claim 1, It is characterized in that The impurities are: iron ≤ 0.25%, silicon ≤ 0.15, carbon ≤ 0.10, nitrogen ≤ 0.05, hydrogen ≤ 0.015%, and oxygen ≤ 0.15%.

3. Preparation method of high temperature alloy materials for manufacturing aircraft engine fasteners, It is characterized in that The steps include: S1, blank forging; S2, grain refinement treatment; S3, intermediate billet forging; S4, forming forging.

4. The method for preparing a high-temperature alloy material for manufacturing aerospace engine fasteners according to claim 3, It is characterized in that In the step S1, the temperature of the forging billet is between 1000 and 1200 degrees, the temperature is kept between 240 minutes and 300 minutes, the total forging ratio is between 18 and 30, and the billet is first air-cooled and then cooled to room temperature for surface treatment.

5. The method for preparing a high temperature alloy material for manufacturing aerospace engine fasteners according to claim 3, It is characterized in that In the step S1, the "melting" is carried out by fusing and mixing the zero-grade titanium sponge with the internal alloy according to the alloy composition set in advance, creating a vacuum environment, and then melting it by electric arc to obtain a ta15 titanium alloy ingot.

6. The method for preparing a high temperature alloy material for manufacturing aerospace engine fasteners according to claim 3, It is characterized in that In the step S1, when the β phase region is upset forged, the preliminary forging blank is placed at tβ+60℃~tβ+80℃ for heating and heat preservation, so as to obtain a higher level forging blank, and then the higher level forging blank is placed at tβ+25℃~tβ+30℃ for heating, so as to obtain a secondary forging blank.

7. The method for preparing a high temperature alloy material for manufacturing aerospace engine fasteners according to claim 3, It is characterized in that In the step S2, the forging machine with a capacity of more than 2000t is used for secondary forging, and the rough surface is heated and kept at 30-70°C below the phase transition point for 300-420min for "refinement treatment". After the first forging deformation, the rough surface is heated and kept at 30-50°C at the phase transition point for 210-300min and then forged again. The forging ratio is controlled between 12-16 and then air-cooled. After cooling, the surface is treated again.

8. The method for preparing a high temperature alloy material for manufacturing aerospace engine fasteners according to claim 3, It is characterized in that In the step S3, the wool pendant is placed at a phase change point of 20-40°C and heated for 240-360 minutes, and a forging deformation is performed. Then, the phase change point is heated at 30-50°C and heated for 210-300 minutes, and the forging ratio is controlled between 12 and 16, and then a surface cleaning treatment is performed.

9. The method for preparing a high temperature alloy material for manufacturing aerospace engine fasteners according to claim 3, It is characterized in that In the step S4, the treated forging blank is placed at 30-50°C for heating and heat preservation, and then placed at 40-70°C for heat preservation for 180-240 minutes after forging for multiple times, and the total forging ratio is controlled between 3.9 and 5.4, followed by air cooling.