Pollution-free device and method for preparing directional structure titanium-aluminum alloy aircraft engine blade

Abstract

The invention provides a pollution-free device and a pollution-free method for preparing a titanium-aluminum alloy aircraft engine blade with a directional structure. The device comprises a furnace body mechanism, a rotary drawing mechanism, a heating and temperature measuring mechanism, a cooling mechanism and an atmosphere protection mechanism, the furnace body mechanism is hollow and is arranged in a sealed mode so that a sample can be placed, and the rotary drawing mechanism comprises an upper connecting disc, a lower connecting disc, a feeding rod and a driving mechanism which is connected with the feeding rod and used for driving the feeding rod to rotate and move up and down; the cooling mechanism is connected with the upper connecting disc and the lower connecting disc to cool the upper connecting disc and the lower connecting disc, the heating and temperature measuring mechanism is used for heating and measuring the temperature of a sample piece placed between the upper connecting disc and the lower connecting disc, and the atmosphere protection mechanism is used for filling argon into a cavity of the furnace body and vacuumizing the cavity. According to the device, circulating directional annealing is carried out on a sample piece, directional solid-state phase change is utilized, the hot forging residual stress is eliminated, meanwhile, the solid-state phase change grain nucleation growth behavior is regulated and controlled, and preparation of the pollution-free high-performance directional structure titanium-aluminum alloy blade is achieved in a pure solid state.

Description

Technical Field

[0001] The present invention relates to the technical field of metal material processing, and in particular to a device and a method for pollution-free preparation of directional structure titanium aluminum alloy aero-engine blades. Background Art

[0002] Titanium aluminum alloy has the advantages of low density, high specific strength, specific stiffness, heat resistance, corrosion resistance and oxidation resistance. It is considered to be an ideal material that can replace nickel-based high-temperature alloys at 650-1000℃ to manufacture aircraft engine blades and improve the thrust-to-weight ratio of aircraft engines and the Mach number of new generation aircraft. Considering that aircraft engine blades are mainly subjected to unidirectional tensile stress during service, and oriented columnar crystals eliminate the transverse grain boundaries that are sensitive to voids and cracks compared to equiaxed crystals, making the stress axis direction parallel to the grain boundaries, how to obtain oriented organization is the key to improving the comprehensive mechanical properties and service life of aircraft engine blades.

[0003] Directional solidification is the most commonly used and mature method to obtain directional structure. However, due to the high activity of titanium-aluminum alloy melt at high temperature, it will react with the mold shell to produce pollution during the long directional solidification process, which will seriously reduce the comprehensive performance of the directional solidification casting. For the smelted titanium-aluminum alloy melt, the conventional casting method is used to make it solidify rapidly. Although it can avoid the serious reaction pollution problem of the alloy melt, there are often many casting defects such as shrinkage cavities and shrinkage in the casting, and the desired directional structure cannot be obtained. At the same time, although the use of hot deformation technology (such as isothermal hot forging) can effectively eliminate the casting defects in the titanium-aluminum alloy ingot and obtain the desired component shape, it still cannot obtain the desired directional structure, and residual stress is easily generated in the component after hot forming, which affects the performance of the component.

[0004] In summary, how to obtain titanium-aluminum alloy blades with directional structure without pollution is the focus and key to improving the comprehensive performance of titanium-aluminum alloy blades and accelerating their practical application. Summary of the invention

[0005] The main purpose of the present invention is to provide a device and method for preparing directional structure titanium aluminum alloy aero-engine blades without pollution, aiming to obtain directional structure titanium aluminum alloy blades without pollution.

[0006] To achieve the above object, the present invention provides a device for preparing directional titanium aluminum alloy aeroengine blades without pollution, including a furnace body mechanism, a rotating and pulling mechanism, a heating and temperature measuring mechanism, a cooling mechanism and an atmosphere protection mechanism, wherein: The furnace body mechanism is hollow and sealed for placing samples. The rotating and pulling mechanism includes an upper connecting plate, a lower connecting plate, a feed rod, and a driving mechanism connected to the feed rod for driving the feed rod to rotate and move up and down. The cooling mechanism is connected to the upper connecting plate and the lower connecting plate to cool both of them. The heating and temperature measuring mechanism is used to heat and measure the temperature of the sample placed between the upper connecting plate and the lower connecting plate. The atmosphere protection mechanism is used to fill argon gas into the chamber of the furnace body and evacuate.

[0007] Preferably, the upper end of the feed rod extends into the interior of the furnace body mechanism, and the lower end is located outside the furnace body mechanism. The driving mechanism includes a linear motor fixedly connected to the bottom of the feed rod, a rotary guide bearing connected to the bottom of the feed rod and arranged in sequence, a coupling, a reducer and a rotary motor.

[0008] Preferably, the rotary pulling mechanism further comprises a rotary connecting mechanism which is located between the upper connecting disk and the lower connecting disk and ensures synchronous rotation of the two.

[0009] Preferably, the rotating connection mechanism includes a vertically arranged first support member, an upper outer gear ring and a lower outer gear ring respectively fixed above and below the first support member, the upper outer gear ring and the lower outer gear ring are respectively connected to the upper connecting plate outer gear ring and the lower connecting plate outer gear ring gear, and the first support member is connected to the fixed member through a linear bearing to achieve that the first support member only rotates in place while moving up and down.

[0010] Preferably, a plurality of rotating connection mechanisms are provided in the circumferential direction of the upper connection disk; the upper part of the sample is connected to the upper connection disk via a graphite disk.

[0011] Preferably, the furnace body mechanism comprises a furnace body with an opening at the upper end, a furnace cover covering the opening of the furnace body, a static seal between the furnace body and the furnace cover, and a dynamic seal between the feed rod and the furnace body.

[0012] Preferably, the heating and temperature measuring mechanism comprises a laser power supply, a fiber laser, a water-cooling cable connecting the laser power supply and the fiber laser, and an infrared temperature measuring gun for measuring the temperature near the heating zone of the sample.

[0013] Preferably, the cooling system includes a first connecting seat and a second connecting seat respectively installed on the feed rod and the upper connecting plate, and water cooling channels are arranged inside the first connecting seat and the second connecting seat. A water cooling channel is arranged on the feed rod, a first sealing ring is installed at the connection between the feed rod and the lower connecting plate, and a second sealing ring is installed at the connection between the second connecting seat and the upper connecting plate.

[0014] Preferably, the atmosphere protection system comprises an argon gas cylinder, a gas filling pipe connecting the argon gas cylinder and the furnace system, and a mechanical pump and a diffusion pump installed on the gas filling pipe, wherein the mechanical pump and the diffusion pump are connected in series.

[0015] The present invention further proposes a method for preparing a directional microstructured titanium aluminum alloy aeroengine blade based on the above-mentioned device without pollution, comprising the following steps: After placing the sample between the upper connecting plate and the lower connecting plate in the furnace body mechanism, close the furnace cover; Open the cooling mechanism, and use the atmosphere protection mechanism to evacuate the furnace chamber of the furnace body mechanism. After the vacuum reaches 10Pa~2Pa, turn off the vacuum pump, open the argon gas bottle of the atmosphere protection mechanism to backfill the furnace chamber with argon protection gas until the furnace chamber pressure reaches -0.06MPa~-0.04MPa; Turn on the heating and temperature measuring mechanism to heat the sample until the surface temperature of the sample heating zone reaches the preset value and stabilizes, keep the power unchanged, and keep warm for 15 min to 30 min; The driving mechanism is started to drive the feed rod to rotate at a constant speed and move downward at a constant speed at a preset speed, thereby driving the sample to pass through the heating zone of the heating and temperature measuring mechanism from bottom to top for directional annealing until the bottom of the heating zone reaches the contact position between the sample and the graphite disk; Turn off the heating and temperature measuring mechanism, and reverse the driving mechanism until the sample rises to its original initial position.

[0016] The device for preparing directional structure titanium aluminum alloy aeroengine blades without pollution proposed by the present invention has the following beneficial effects: (1) The use of a heating and temperature measuring mechanism can achieve cyclic directional annealing. While eliminating hot forging stress, the directional solid-state phase transformation is used to achieve the growth of directional columnar crystals in a pure solid state, thereby obtaining a titanium-aluminum alloy aero-engine blade with a directional structure. Since the entire long process of columnar crystal growth is carried out in a pure solid state under the protection of an inert atmosphere, the reaction contamination problem caused by the high high-temperature activity of titanium-aluminum alloys is avoided; (2) Both the upper and lower parts of the sample are cooled, that is, when the sample moves downward for directional annealing, corresponding axial temperature gradients are established at the heating front and the cooling front. The establishment of biaxial temperature gradients is beneficial to the directional solid-state phase transformation and directional columnar crystal growth of the titanium-aluminum alloy blade sample; (3) The sample moves downward as the feed rod rotates and gradually passes through the heating zone, which is beneficial to improving the uniformity of the circumferential temperature of the heating zone of the sample, thereby reducing the residual stress in the sample after cyclic directional annealing while achieving directional solid-state phase transformation and directional columnar crystal growth; (4) The device of the present invention has the advantages of simple structure, high control accuracy and strong operability. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of the structure of the device for pollution-free preparation of directional microstructure titanium-aluminum alloy aeroengine blades according to the present invention; Figure 2The schematic diagram of the top view of the structure of the rotary pulling mechanism in the device for pollution-free preparation of directional structure titanium aluminum alloy aero-engine blades of the present invention.

[0018] In the figure, 1-furnace body mechanism; 11-furnace cover; 12-static seal; 13-furnace body; 14-infrared temperature measuring window; 15-dynamic seal; 2-rotating pull-out mechanism; 21-feed rod; 22-graphite disk; 23-linear linear motor; 24-rotating guide bearing; 25-coupling; 26-reducer; 27-rotating motor; 281-first sealing ring; 282-second sealing ring; 291-lower connecting plate; 292-upper connecting plate; 2101-lower connecting plate outer gear ring; 2102-upper connecting plate outer gear ring; 2111-lower outer gear ring; 2112-upper outer gear ring; 212-support; 213-linear bearing; 214-fixing part; 215-sample; 3-heating and temperature measuring mechanism; 31-laser power supply; 32-water cooling cable; 33-fiber laser; 34-infrared temperature measuring gun; 4-cooling mechanism; 411-first circulating water cooling channel; 412-second circulating water cooling channel; 421-first connecting seat; 422-second connecting seat; 5-atmosphere protection mechanism; 51-mechanical pump; 52-diffusion pump; 53-argon gas bottle; 2121-first support; 2122-second support; 2123-third support.

[0019] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0020] It should be understood that the specific embodiments described herein are only used to explain the present invention, and are not used to limit the present invention.

[0021] It should be noted that in the description of the present invention, the terms "transverse", "longitudinal", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate the orientation or position relationship based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second" and the like are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0022] Reference Figure 1 In this preferred embodiment, a device for preparing directional structure titanium aluminum alloy aircraft engine blades without pollution includes a furnace body mechanism 1, a rotating and pulling mechanism 2, a heating and temperature measuring mechanism 3, a cooling mechanism 4 and an atmosphere protection mechanism 5, wherein: The furnace body mechanism 1 is hollow and sealed for placing the sample 215. The rotating and pulling mechanism 2 includes an upper connecting plate 292, a lower connecting plate 292, a feed rod 21, and a driving mechanism connected to the feed rod 21 for driving it to rotate and move up and down. The cooling mechanism 4 is connected to the upper connecting plate 292 and the lower connecting plate 292 to cool both of them. The heating and temperature measuring mechanism 3 is used to heat and measure the temperature of the sample 215 placed between the upper connecting plate 292 and the lower connecting plate 292. The atmosphere protection mechanism 5 is used to fill argon gas into the chamber of the furnace body and evacuate.

[0023] Specifically, in this embodiment, the upper end of the feed rod 21 extends into the interior of the furnace body mechanism 1, and the lower end is located outside the furnace body mechanism 1. The driving mechanism includes a linear motor 23 fixedly connected to the bottom of the feed rod 21, a rotary guide bearing 24 connected to the bottom of the feed rod 21 and arranged in sequence, a coupling 25, a reducer 26 and a rotary motor 27. This structure realizes the up and down movement and rotation of the feed rod 21.

[0024] Furthermore, the rotary pull-out mechanism 2 further comprises a rotary connection mechanism located between the upper connection disk 292 and the lower connection disk 292 and ensuring that the two rotate synchronously. The rotary connection mechanism ensures that the upper connection disk 292 and the lower connection disk 292 rotate synchronously.

[0025] This embodiment proposes a specific structure of a rotating connection mechanism: the rotating connection mechanism includes a vertically arranged first support member 2121, an upper outer gear ring 2112 and a lower outer gear ring 2111 respectively fixed above and below the first support member 2121, the upper outer gear ring 2112 and the lower outer gear ring 2111 are respectively connected to the upper connecting plate outer gear ring 2102 and the lower connecting plate outer gear ring 2102, and the first support member 2121 is connected to the fixing member 214 through a linear bearing 213 to achieve that the first support member 2121 only rotates in place while moving up and down.

[0026] Furthermore, a plurality of rotating connection mechanisms are provided in the circumferential direction of the upper connection disk 292 so as to stably support the upper connection disk 292 thereon. Figure 2 Taking the provision of three or more rotating connection mechanisms as an example for specific description, in this case, they are respectively a first support member 2121, a second support member 2122 and a third support member 2123. The first support member 2121, the second support member 2122 and the third support member 2123 are collectively referred to as the support member 212.

[0027] The top of the sample 215 is connected to the upper connecting plate 292 via the graphite plate 22 .

[0028] In this embodiment, the furnace body mechanism 1 includes a furnace body 13 with an opening at the upper end, a furnace cover 11 covering the opening of the furnace body 13, a static seal 12 located between the furnace body 13 and the furnace cover 11, and a dynamic seal 15 located between the feed rod 21 and the furnace body 13. An infrared temperature measuring window 14 is provided on the furnace body 13.

[0029] In this embodiment, the heating and temperature measuring mechanism 3 includes a laser power supply 31, a fiber laser 33, a water-cooling cable 32 connecting the laser power supply 31 and the fiber laser 33, and an infrared temperature measuring gun 34 for measuring the temperature near the heating zone of the sample 215. The fiber laser 33 is used for heating the hot-forged titanium-aluminum alloy aeroengine blade sample 215; the infrared temperature measuring gun 34 is used for measuring and regulating the temperature near the heating zone of the sample 215.

[0030] In this embodiment, the cooling system includes a first connection seat 421 and a second connection seat 422 respectively installed on the feed rod 21 and the upper connection plate, and water cooling channels are arranged inside the first connection seat 421 and the second connection seat 422. The feed rod 21 is provided with a water cooling channel, and a first sealing ring 281 is installed at the connection between the feed rod 21 and the lower connection plate 292, and a second sealing ring 282 is installed at the connection between the second connection seat 422 and the upper connection plate 292. The first sealing ring 281 and the second sealing ring 282 ensure the sealing of the cooling water in the connection plate. The first connection seat 421 has a first circulating water cooling channel 411 inside, and the second connection seat 422 has a second circulating water cooling channel 412 inside.

[0031] The lower connecting plate 292 is used to form an axial temperature gradient on the lower part of the sample 215 , and the upper connecting plate 292 is used to form an axial temperature gradient on the upper part of the sample 215 , and the axial temperature gradient on the lower part is opposite to the axial temperature gradient on the upper part of the sample 215 .

[0032] In this embodiment, the atmosphere protection system includes an argon gas bottle 53, a gas charging pipe connecting the argon gas bottle 53 and the furnace system, and a mechanical pump 51 and a diffusion pump 52 installed on the gas charging pipe, and the mechanical pump 51 is connected in series with the diffusion pump 52. The argon gas bottle 53 is connected to the furnace of the furnace body and is used to fill the furnace of the furnace body with argon gas after vacuum extraction, so as to achieve inert gas protection during the heat treatment process of the sample 215 to prevent it from being oxidized.

[0033] The specific method of using the device for preparing directional structure titanium aluminum alloy aeroengine blades without pollution is as follows: 1. Open the furnace cover 11, assemble the connecting plate, blades, graphite plate 22, first support member 2121 and other components in the furnace body according to the above assembly relationship, and close the furnace cover 11; 2. Turn on the circulating cooling water and start the mechanical pump 51 and the diffusion pump 52 in turn to draw a vacuum to the furnace body and furnace chamber. After the vacuum reaches 10Pa to 2Pa, turn off the vacuum pump and start the argon gas bottle 53 to backfill the furnace chamber with argon protective gas until the furnace chamber pressure reaches -0.06 MPa to -0.04 MPa. 3. Turn on the laser power 31 and gradually increase the laser power at a rate of 100 W / min until the surface temperature (infrared temperature reading) of the heating zone of the aircraft engine sample 215 reaches the preset value (1450°C~1500°C) and stabilizes, keep the power unchanged, and keep warm for 15~30 minutes; 4. Turn on the linear motor 23 and the rotary motor 27, so that they drive the feed rod 21 to rotate at a constant speed at a preset speed and move downward steadily (the downward movement speed is 0.2-0.5 mm / min), thereby driving the sample 215 to pass through the laser heating zone from bottom to top for directional annealing, until the bottom of the laser heating zone reaches the contact position between the top of the sample 215 and the graphite disk 22; 5. Turn on the laser power supply 31, and reverse the linear motor 23 and the rotary motor 27 until the sample 215 rises to the original initial position; 6. Repeat steps 3 to 4 3 to 5 times, turn off the laser power supply 31, the linear motor and the rotary motor 27, stop the circulating water cooling after the sample 215 is completely cooled, open the air release valve of the furnace body 13, open the furnace cover 11 and take out the processed sample 215.

[0034] The device for preparing directional structure titanium aluminum alloy aeroengine blades without pollution proposed by the present invention has the following beneficial effects: (1) The use of the heating and temperature measuring mechanism 3 can realize cyclic directional annealing, and while eliminating the hot forging stress, the directional solid-state phase transformation is used to realize the growth of directional columnar crystals in a pure solid state, thereby obtaining a titanium-aluminum alloy aero-engine blade with a directional structure. Since the entire long-term process of columnar crystal growth is carried out in a pure solid state under the protection of an inert atmosphere, the reaction contamination problem caused by the high high-temperature activity of titanium-aluminum alloy is avoided; (2) Both the upper and lower parts of the sample 215 are cooled, that is, when the sample 215 moves downward for directional annealing, corresponding axial temperature gradients are established at the heating front and the cooling front. The establishment of a biaxial temperature gradient is beneficial to the directional solid-state phase transformation and directional columnar crystal growth of the titanium-aluminum alloy blade sample 215; (3) The sample 215 moves downward as the feed rod 21 rotates and gradually passes through the heating zone, which is beneficial to improving the uniformity of the circumferential temperature of the heating zone of the sample 215, thereby reducing the residual stress in the sample 215 after cyclic directional annealing while achieving directional solid-state phase transformation and directional columnar crystal growth; (4) The device of the present invention has the advantages of simple structure, high control accuracy and strong operability.

[0035] The present invention further proposes a method for preparing a device for directional structure titanium aluminum alloy aero-engine blades without pollution.

[0036] In this preferred embodiment, a method for preparing a device for non-polluting oriented titanium-aluminum alloy aeroengine blades based on the above-mentioned device comprises the following steps: Step S1, after placing the sample 215 between the upper connecting plate 292 and the lower connecting plate 292 in the furnace body mechanism 1, the furnace cover 11 is closed; Step S2, open the cooling mechanism 4, and evacuate the furnace chamber of the furnace body mechanism 1 through the atmosphere protection mechanism 5, and after the vacuum is evacuated to 10Pa~2Pa, turn off the vacuum pump, open the argon gas bottle 53 of the atmosphere protection mechanism 5 to backfill the furnace chamber with argon protection gas until the furnace chamber pressure reaches -0.06MPa~-0.04MPa; Step S3, turning on the heating and temperature measuring mechanism 3 to heat the sample 215 until the surface temperature of the heating zone of the sample 215 reaches a preset value and stabilizes, keeping the power supply unchanged, and keeping the temperature for 15 min to 30 min; Step S4, start the driving mechanism to drive the feeding rod 21 to rotate at a constant speed and move downward at a constant speed at a preset speed, thereby driving the sample 215 to pass through the heating zone of the heating and temperature measuring mechanism 3 from bottom to top for directional annealing until the bottom of the heating zone reaches the contact position between the sample and the graphite disk 22; Step S5, turning off the heating and temperature measuring mechanism 3, and reversing the driving mechanism until the sample 215 rises to the original initial position.

[0037] Repeat steps S3 to S4 for 3 to 5 times, turn off the heating and temperature measuring mechanism 3 and the driving mechanism, stop circulating water cooling after the sample 215 is completely cooled, open the air valve, open the furnace cover 11 and take out the processed sample 215.

[0038] The present invention proposes a preparation method that avoids long-term directional solidification, and adopts cyclic directional annealing for the near-net-shaped titanium-aluminum alloy blades after hot forging after rapid solidification. While eliminating the hot forging stress, it utilizes directional solid-state phase transformation to achieve the growth of directional columnar crystals in pure solid state, thereby obtaining directional structure titanium-aluminum alloy aero-engine blades. Since the long-term process of the entire columnar crystal growth is carried out in pure solid state under the protection of an inert atmosphere, the reaction pollution problem existing in titanium-aluminum alloys due to their high high-temperature activity is avoided.

[0039] The above are only preferred embodiments of the present invention, and are not intended to limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A device for preparing directional structure titanium aluminum alloy aircraft engine blades without pollution, characterized in that: It includes a furnace body mechanism, a rotating and pulling mechanism, a heating and temperature measuring mechanism, a cooling mechanism and an atmosphere protection mechanism, among which: The furnace body mechanism is hollow and sealed for placing samples. The rotating and pulling mechanism includes an upper connecting plate, a lower connecting plate, a feed rod, and a driving mechanism connected to the feed rod for driving the feed rod to rotate and move up and down. The cooling mechanism is connected to the upper connecting plate and the lower connecting plate to cool the two. The heating and temperature measuring mechanism is used to heat and measure the temperature of the sample placed between the upper connecting plate and the lower connecting plate. The atmosphere protection mechanism is used to fill argon gas into the chamber of the furnace body and evacuate the vacuum. The rotating and pulling mechanism and the heating and temperature measuring mechanism work together to achieve sequential heating of the sample in the height direction, thereby realizing cyclic directional annealing.

2. The pollution-free device for preparing directional structure titanium aluminum alloy aeroengine blades according to claim 1 is characterized in that: The upper end of the feed rod extends into the interior of the furnace body mechanism, and the lower end of the feed rod is located outside the furnace body mechanism. The driving mechanism includes a linear motor fixedly connected to the bottom of the feed rod, a rotary guide bearing connected to the bottom of the feed rod and arranged in sequence, a coupling, a reducer and a rotary motor.

3. The pollution-free device for preparing directional structure titanium aluminum alloy aeroengine blades according to claim 1 is characterized in that: The rotary pulling mechanism also includes a rotary connecting mechanism located between the upper connecting disk and the lower connecting disk and ensuring synchronous rotation of the two.

4. The device for non-polluting preparation of directional structure titanium aluminum alloy aeroengine blades as claimed in claim 3, characterized in that: The rotating connection mechanism includes a vertically arranged first support member, an upper outer gear ring and a lower outer gear ring respectively fixed above and below the first support member, the upper outer gear ring and the lower outer gear ring are respectively connected to the upper connecting plate outer gear ring and the lower connecting plate outer gear ring gear, and the first support member is connected to the fixed member through a linear bearing to achieve that the first support member only rotates in place while moving up and down.

5. The device for non-polluting preparation of directional microstructured titanium-aluminum alloy aeroengine blades as claimed in claim 3, characterized in that: The upper connecting plate is provided with a plurality of rotating connecting mechanisms in the circumferential direction; the upper part of the sample is connected to the upper connecting plate through a graphite plate.

6. The pollution-free device for preparing directional structure titanium aluminum alloy aeroengine blades according to claim 1, characterized in that: The furnace body mechanism comprises a furnace body with an upper opening, a furnace cover covering the furnace body opening, a static seal between the furnace body and the furnace cover, and a dynamic seal between the feed rod and the furnace body.

7. The device for non-polluting preparation of directional structure titanium aluminum alloy aeroengine blades according to claim 1, characterized in that: The heating and temperature measuring mechanism comprises a laser power supply, a fiber laser, a water-cooling cable connecting the laser power supply and the fiber laser, and an infrared temperature measuring gun for measuring the temperature near the heating zone of the sample.

8. The pollution-free device for preparing directional structure titanium aluminum alloy aeroengine blades according to claim 1 is characterized in that: The cooling system includes a first connecting seat and a second connecting seat respectively installed on the feed rod and the upper connecting plate, and water cooling channels are arranged inside the first connecting seat and the second connecting seat. A water cooling channel is arranged on the feed rod, a first sealing ring is installed at the connection between the feed rod and the lower connecting plate, and a second sealing ring is installed at the connection between the second connecting seat and the upper connecting plate.

9. The device for non-polluting preparation of directional microstructured titanium-aluminum alloy aeroengine blades according to any one of claims 1 to 8, characterized in that: The atmosphere protection system comprises an argon gas cylinder, a gas charging pipeline connecting the argon gas cylinder and the furnace system, and a mechanical pump and a diffusion pump installed on the gas charging pipeline, wherein the mechanical pump and the diffusion pump are connected in series.

10. A method for non-polluting preparation of the device for directional structure titanium aluminum alloy aeroengine blades according to claim 1, characterized in that: The following steps are involved: After placing the sample between the upper connecting plate and the lower connecting plate in the furnace body mechanism, close the furnace cover; Open the cooling mechanism, and use the atmosphere protection mechanism to evacuate the furnace chamber of the furnace body mechanism. After the vacuum reaches 10Pa~2Pa, turn off the vacuum pump, open the argon gas bottle of the atmosphere protection mechanism to backfill the furnace chamber with argon protection gas until the furnace chamber pressure reaches -0.06MPa~-0.04MPa; Turn on the heating and temperature measuring mechanism to heat the sample until the surface temperature of the sample heating zone reaches the preset value and stabilizes, keep the power unchanged, and keep warm for 15 min to 30 min; The driving mechanism is started to drive the feed rod to rotate at a constant speed and move downward at a constant speed at a preset speed, thereby driving the sample to pass through the heating zone of the heating and temperature measuring mechanism from bottom to top for directional annealing until the bottom of the heating zone reaches the contact position between the sample and the graphite disk; Turn off the heating and temperature measuring mechanism, and reverse the driving mechanism until the sample rises to its original initial position.

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