A high-temperature alloy casting device and casting method for an aircraft

Abstract

The present invention discloses a superalloy casting device and a casting method for an aircraft, belonging to the technical field of metal casting processing. It includes a sandblasting pipe, and also includes: a mixing chamber fixedly installed in the sandblasting pipe, a sand outlet is provided at the sand outlet end of the sandblasting pipe, and a mixing pipe is fixedly connected between the sand outlet and the mixing chamber; an anti-slip seat fixedly installed on the sandblasting pipe, extrusion parts are symmetrically installed in the anti-slip seat, a transmission shaft is connected between the two extrusion parts, and the output end of the extrusion part is fixedly connected to the mixing pipe; a motor is fixedly installed on the sandblasting pipe, the output end of the motor is in transmission connection with the extrusion parts on both sides, the output end of the motor drives the transmission shaft to rotate, the transmission shaft transmits the rotating force to the extrusion parts at both ends, so that the air in the extrusion parts is squeezed into the mixing pipes on both sides, providing an acceleration for the sand and gravel in the mixing pipes and increasing the flow velocity of the sand and gravel ejected from the sides.

Description

Technical Field

[0001] The present invention relates to the technical field of metal casting and processing, and particularly relates to a high-temperature alloy casting device and a casting method for an aircraft. Background Art

[0002] Magnesium alloy is an alloy composed of magnesium as the base and other elements added. Its characteristics are: low density, high strength, large elastic modulus, good heat dissipation, good shock absorption, greater ability to withstand impact loads than aluminum alloy, and good corrosion resistance to organic substances and alkalis. It is widely used in the manufacture of aircraft.

[0003] After the fixed-wing structural member made of magnesium alloy material is cast, its surface needs to be polished with 120# fine sand and then anodized to increase the corrosion resistance and high-temperature resistance of the fixed-wing structural member and other properties.

[0004] Since there are multiple grooves arranged in parallel on the surface of the fixed-wing structural member, when a general sandblasting device is used for polishing, it cannot effectively polish the inside of the grooves, resulting in poor subsequent oxidation treatment effect. Summary of the Invention

[0005] The purpose of the present invention is to solve the problem in the prior art that due to the presence of multiple grooves arranged in parallel on the surface of the fixed-wing structural member, when a general sandblasting device is used for polishing, it cannot effectively polish the inside of the grooves, resulting in poor subsequent oxidation treatment effect, and to propose a high-temperature alloy casting device and a casting method for an aircraft.

[0006] In order to achieve the above purpose, the present invention adopts the following technical scheme:

[0007] A high-temperature alloy casting device for an aircraft, including a sandblasting pipe, and further including: a mixing chamber fixedly installed in the sandblasting pipe, an outlet opening is provided at the sand outlet end of the sandblasting pipe, and a mixing pipe is fixedly connected between the outlet opening and the mixing chamber; the outlet opening includes a first sand opening located at the center of the sandblasting pipe and second sand openings symmetrically arranged on the left and right; an anti-slip seat fixedly installed on the sandblasting pipe, an extrusion part is symmetrically installed in the anti-slip seat, a transmission shaft is connected between the two extrusion parts, and the output end of the extrusion part is fixedly connected to the mixing pipe on the second sand opening; a motor is fixedly installed on the sandblasting pipe, and the output end of the motor is in transmission connection with the extrusion parts on both sides.

[0008] Preferably, a first bevel gear is fixedly installed at the output end of the motor, a second bevel gear is fixedly installed on the transmission shaft, and the first bevel gear and the second bevel gear are meshed and connected.

[0009] In order to squeeze the air in the airbag into the mixing pipe and increase the flow rate of the grit in the two mixing pipes on both sides, preferably, the squeezing part includes: a first sliding plate and a second sliding plate slidably installed in the anti-slip seat, an upper pressing plate and a lower pressing plate are respectively fixedly installed on the first sliding plate and the second sliding plate, an airbag is fixedly installed on the lower pressing plate, and an air outlet pipe is fixedly connected between the airbag and the mixing pipe; a vane is rotatably connected between the first sliding plate and the second sliding plate; a first gear is fixedly installed on the vane, and a second gear is fixedly installed at one end of the transmission shaft located in the anti-slip seat, and the first gear is meshed with the second gear.

[0010] In order to effectively prevent grit from entering the airbag, further, an air inlet pipe is fixedly installed on the airbag, and a filter screen and a two-way valve are fixedly installed in the air inlet pipe.

[0011] In order to make the flow direction of the air outlet pipe consistent with the mixing pipe and not disturb the sorting of the grit in the mixing pipe, further, the working surface of the air outlet pipe faces the sand outlet.

[0012] In order to effectively improve the sandblasting effect, further, it further includes: a limiting plate slidably installed on the sandblasting pipe, and a resisting rod fixedly installed on the lower pressing plate and abutted against the limiting plate.

[0013] In order to improve the mixing of compressed air and grit, preferably, it further includes: a piston plate slidably installed in the mixing chamber, a connecting column is fixedly installed on the piston plate, the upper end of the connecting column penetrates through the mixing chamber and a driving plate is fixedly installed; a cam is fixedly installed on the transmission shaft, and the cam is in contact with the driving plate.

[0014] In order to effectively prevent grit from caking, further, it further includes: a rotating shaft rotatably installed on the piston plate, a disc and a third gear are fixedly installed on the rotating shaft, and a rack adapted to the third gear is fixedly installed on the inner wall of the mixing chamber; knocking blocks are uniformly installed on the disc along the circumferential direction.

[0015] In order to leave a spraying distance between the first sand outlet and the fixed wing, further, it further includes: an adjusting rod threadedly installed in the anti-slip seat, a roller is fixedly installed at the lower end of the adjusting rod; the limiting plate is elastically installed on the adjusting rod.

[0016] A casting method for superalloy for aircraft is as follows:

[0017] Step 1: Place the fixed wing in the sandblasting box;

[0018] Step 2: Perform sandblasting treatment on the surface of the fixed wing;

[0019] Step 3: Perform sandblasting treatment on the gaps on the fixed wing.

[0020] Compared with the prior art, the present invention provides a superalloy casting device and a casting method for aircraft, having the following beneficial effects:

[0021] 1. For the superalloy casting device for aircraft, driven by a motor, the first slide plate and the second slide plate drive the upper pressing plate and the lower pressing plate to approach each other to squeeze the airbag. The air in the airbag is pressurized and quickly enters the mixing pipe through the air outlet pipe, providing an acceleration for the grit in the mixing pipe, increasing the flow rate of the grit ejected from the side, effectively reducing the sandblasting dead angle. At the same time, the lower pressing plate pushes the limiting plate to move up and down quickly through the resisting rod. The limiting plate is located above the second sand outlet. When the grit is ejected from the second sand outlet, it is blocked by the limiting plate, so that all of it acts on the fixed wing, improving the sandblasting efficiency;

[0022] 2. For the superalloy casting device for aircraft, the grit and high-pressure air are transported to the mixing chamber through an externally connected pipeline. The cam on the transmission shaft intermittently squeezes the driving plate, so that the driving plate pushes the piston plate inside the mixing chamber to slide up and down through the connecting column. The sliding piston plate provides a preliminary acceleration for the grit, enabling the grit and the compressed air to quickly enter the mixing pipe;

[0023] 3. For the superalloy casting device for aircraft, during the downward pressing of the piston plate, the third gear meshes with the rack and rotates. The rotating third gear transmits the rotating force to the rotating shaft, so that the rotating shaft drives the disc to rotate. The rotating disc uses centrifugal force to interfere with the internal grit to prevent the grit from caking;

[0024] 4. For the superalloy casting device for aircraft, when sandblasting the groove on the fixed wing, the roller contacts the inner top surface of the groove on the fixed wing, leaving a gap between the sandblasting pipe and the inner bottom surface of the groove, avoiding damage to the fixed wing itself caused by excessive sandblasting. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 is a schematic structural diagram of a superalloy casting device for aircraft proposed by the present invention;

[0026] Figure 2 is a schematic second perspective structural diagram of a superalloy casting device for aircraft proposed by the present invention;

[0027] Figure 3 is a schematic third perspective structural diagram of a superalloy casting device for aircraft proposed by the present invention;

[0028] Figure 4 is a superalloy casting device for aircraft proposed by the present invention Figure 1 schematic structural diagram of part A therein;

[0029] Figure 5 is a superalloy casting device for aircraft proposed by the present inventionFigure 2 Schematic diagram of part B

[0030] Figure 6 A high-temperature alloy casting device for aircraft proposed by the present invention Figure 3 Schematic diagram of part C

[0031] Figure 7 Schematic diagram of the fixed wing of a high-temperature alloy casting device for aircraft proposed by the present invention

[0032] In the figure: 1, sandblasting pipe; 2, mixing chamber; 3, sand outlet; 301, first sand outlet; 302, second sand outlet; 4, mixing pipe; 5, anti-slip seat; 6, two-way valve; 7, rotating shaft; 8, first slide plate; 9, second slide plate; 10, upper pressing plate; 11, airbag; 12, air outlet pipe; 13, blade plate; 14, first gear; 15, motor; 16, first conical tooth; 17, transmission shaft; 18, second conical tooth; 19, second gear; 20, lower pressing plate; 21, limiting plate; 22, piston plate; 23, connecting column; 24, driving plate; 25, cam; 26, resisting rod; 27, disc; 28, third gear; 29, rack; 30, knocking block; 3001, third spring; 3002, block; 31, adjusting rod; 32, air inlet pipe; 33, roller; 34, filter screen; 35, connecting rod; 36, first spring; 37, second spring. Specific embodiments

[0033] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments.

[0034] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0035] Embodiment 1:

[0036] Refer to Figures 1-7, a high-temperature alloy casting device for an aircraft, including a long sandblasting pipe 1, and further including: a mixing chamber 2 fixedly installed inside the sandblasting pipe 1, a sand outlet 3 is provided at the sand outlet end of the sandblasting pipe 1, and a mixing pipe 4 is fixedly connected between the sand outlet 3 and the mixing chamber 2; the sand outlet 3 includes a first sand outlet 301 located at the center of the sandblasting pipe 1 and second sand outlets 302 that are symmetric left and right. In this solution, 120# fine sand is used for sandblasting and polishing the fixed wing of the UAV to facilitate subsequent anodic oxidation treatment. The shape of the fixed wing is as Figure 7 , since a plurality of straight grooves are equidistantly arranged on the fixed wing, in order to reduce sandblasting dead angles, the long sandblasting pipe 1 can penetrate into the grooves, and the symmetric second sand outlets 302 on the left and right can sandblast the side groove walls of the grooves; an anti-slip seat 5 fixedly installed on the sandblasting pipe 1, anti-slip patterns are uniformly arranged on the outer edge surface of the anti-slip seat 5, and extrusion parts are symmetrically installed inside the anti-slip seat 5. A transmission shaft 17 is connected between the two extrusion parts, and the output end of the extrusion part is fixedly connected to the mixing pipe 4 on the second sand outlet 302; a motor 15 is fixedly installed on the sandblasting pipe 1, and the output end of the motor 15 is drivingly connected to the extrusion parts on both sides.

[0037] The first sand outlet 301 can sandblast the bottom surface of the groove, and the second sand outlets 302 on both sides can sandblast the side groove walls of the groove. Since the mixing pipes 4 on both sides are bent pipes, the flow rate of the high-pressure air will decrease when passing through the bent pipes compared to the straight pipe in the middle. Therefore, new air needs to be added to the bent pipes on both sides to increase the flow rate.

[0038] Refer to Figure 3 , a first conical gear 16 is fixedly installed at the output end of the motor 15, a second conical gear 18 is fixedly installed on the transmission shaft 17, and the first conical gear 16 and the second conical gear 18 are meshed and connected.

[0039] During the operation of the motor 15, the output end of the motor 15 drives the first conical gear 16 to rotate. The rotating first conical gear 16 drives the meshed second conical gear 18 to rotate. The second conical gear 18 transmits the rotating force to the extrusion parts at both ends through the transmission shaft 17, so that the air in the extrusion parts is squeezed into the mixing pipes 4 on both sides, providing an acceleration to the sand grains in the mixing pipes 4 and increasing the flow rate of the sand grains ejected from the sides.

[0040] Refer to Figure 1 and Figure 2 and Figure 3 and Figure 5 , for the extrusion part in this solution, further optimization has been carried out.

[0041] The extrusion part includes: a first slide plate 8 and a second slide plate 9 slidably mounted in the anti-slip seat 5. An upper pressure plate 10 and a lower pressure plate 20 are respectively and fixedly mounted on the first slide plate 8 and the second slide plate 9. An air bag 11 is fixedly mounted on the lower pressure plate 20. An air outlet pipe 12 is fixedly connected between the air bag 11 and the mixing pipe 4. A vane 13 is rotatably connected between the first slide plate 8 and the second slide plate 9. A first gear 14 is fixedly mounted on the vane 13. One end of the transmission shaft 17 located in the anti-slip seat 5 is fixedly mounted with a second gear 19. The first gear 14 is meshed and connected with the second gear 19.

[0042] It should be noted that the vane 13 includes two parts. One is the plate body fixed together with the first gear 14, and the other is the connecting rods rotatably connected at both ends of the plate body. The ends of the two connecting rods away from the plate body are respectively rotatably connected with the first slide plate 8 and the second slide plate 9. In this way, when the plate body rotates, the connecting rods at both ends can pull the first slide plate 8 and the second slide plate 9 closer to or away from each other.

[0043] During the rotation of the transmission shaft 17, the second gears 19 at both ends drive the meshed first gear 14 to rotate. The rotating first gear 14 drives the meshed second gear 19 to rotate. During the rotation of the second gear 19, the first slide plate 8 and the second slide plate 9 drive the upper pressure plate 10 and the lower pressure plate 20 to approach each other to squeeze the air bag 11. The air in the air bag 11 is pressurized and quickly enters the mixing pipe 4 through the air outlet pipe 12, providing an acceleration to the gravel in the mixing pipe 4 and increasing the flow rate of the gravel ejected from the side.

[0044] Connecting rods 35 are fixedly mounted on both sides of the first slide plate 8 and the second slide plate 9. The upper pressure plate 10 and the lower pressure plate 20 are both fixed together with the connecting rods 35. And the connecting rod 35 on the first slide plate 8 slides in the upper pressure plate 10, playing a limiting role in the sliding of the connecting rod 35. And a first spring 36 is sleeved on the connecting rod 35 on the first slide plate 8. The two ends of the first spring 36 are respectively fixedly connected with the upper pressure plate 10 and the lower pressure plate 20, facilitating the reset of the vane 13.

[0045] Refer to Figure 4 Furthermore, an air inlet pipe 32 is fixedly mounted on the air bag 11. A filter screen 34 and a two-way valve 6 are fixedly mounted in the air inlet pipe 32.

[0046] After the air bag 11 is compressed by force, new air needs to be supplemented through the air inlet pipe 32. Since there is more gravel in the sandblasting box, a filter screen 34 needs to be installed in the air inlet pipe 32 to prevent the gravel from entering the air bag 11. A one-way valve is fixedly mounted in the air outlet pipe 12 to prevent the gas from flowing back from the air outlet pipe 12 when the air bag 11 intakes air.

[0047] Since the surface of the filter screen 34 will be attached with grit after long-term use, the two-way valve 6 installed can make part of the gas blow towards the filter screen 34 when the airbag 11 is compressed, avoiding the blockage of the filter screen 34.

[0048] It should be noted that the air inlet end of the two-way valve is larger than the air outlet end, reducing the air discharge volume so that most of the air is discharged from the air outlet pipe 12.

[0049] Refer to Figure 3 , in order to prevent the air in the airbag 11 from entering the mixing pipe 4 and disturbing the flow sequence of the grit, furthermore, the working surface of the air outlet pipe 12 faces the sand outlet 3.

[0050] Refer to Figure 1 , the high-temperature alloy casting device for aircraft in this embodiment further includes: a limit plate 21 slidably installed on the sandblasting pipe 1, and a resisting rod 26 fixedly installed on the lower pressing plate 20 and abutted against the limit plate 21.

[0051] During the extrusion of the airbag 11, the lower pressing plate 20 pushes the limit plate 21 to move up and down quickly through the resisting rod 26. The limit plate 21 is located above the second sand outlet 302. When the grit is ejected from the second sand outlet 302, it is blocked by the limit plate 21, so that all of it acts on the fixed wing, improving the sandblasting efficiency.

[0052] Generally speaking, when casting and producing the fixed wing for the machine, it is necessary to perform sandblasting treatment on the surface of the fixed wing to facilitate subsequent anodic oxidation, thereby improving the corrosion resistance, hardness and wear resistance of the metal. Since a plurality of straight grooves are equidistantly arranged on the fixed wing, the long strip-shaped sandblasting pipe 1 can extend into the grooves. The output end of the motor 15 drives the first conical tooth 16 to rotate, and the rotating first conical tooth 16 drives the meshing-connected second conical tooth 18 to rotate. The second conical tooth 18 transmits the rotating force to the second gears 19 at both ends through the transmission shaft 17. The second gears 19 drive the meshing-connected first gears 14 to rotate. During the rotation of the first gears 14, the first sliding plate 8 and the second sliding plate 9 drive the upper pressing plate 10 and the lower pressing plate 20 to approach each other to squeeze the airbag 11. The air in the airbag 11 is pressurized and quickly enters the mixing pipe 4 through the air outlet pipe 12, providing an acceleration for the grit in the mixing pipe 4, increasing the flow rate of the grit ejected from the side, and effectively reducing the sandblasting dead angle.

[0053] Embodiment 2:

[0054] Refer to Figures 1-7 , which is basically the same as Embodiment 1. On the basis of Embodiment 1, the entire technical solution is further optimized.

[0055] Refer to Figure 3 and Figure 6, in order to improve the uniformity of the mixture of grit and high-pressure air during sandblasting, the aircraft superalloy casting device in this embodiment further includes: a piston plate 22 slidably installed in the mixing chamber 2, an adapter column 23 fixedly installed on the piston plate 22, the upper end of the adapter column 23 penetrates through the mixing chamber 2 and is fixedly installed with a drive plate 24; a cam 25 is fixedly installed on the transmission shaft 17, and the cam 25 is in contact with the drive plate 24.

[0056] The grit and high-pressure air are conveyed into the mixing chamber 2 through an external pipeline. The cam 25 on the transmission shaft 17 intermittently presses the drive plate 24, so that the drive plate 24 pushes the piston plate 22 inside the mixing chamber 2 to slide up and down through the adapter column 23. The sliding piston plate 22 provides a preliminary acceleration for the grit, so that the grit and compressed air quickly enter the mixing pipe 4.

[0057] A second spring 37 is sleeved on the adapter column 23, and both ends of the second spring 37 are fixedly connected to the drive plate 24 and the top surface of the mixing chamber 2 respectively to help the piston plate 22 reset.

[0058] Refer to Figure 6 , the aircraft superalloy casting device in this embodiment further includes: a rotating shaft 7 rotatably installed on the piston plate 22, a disc 27 and a third gear 28 are fixedly installed on the rotating shaft 7, and a rack 29 adapted to the third gear 28 is fixedly installed on the inner wall of the mixing chamber 2; a plurality of knocking blocks 30 are evenly installed on the disc 27 along the circumferential direction.

[0059] During the downward pressing of the piston plate 22, the third gear 28 is meshed with the rack 29 and rotates. The rotating third gear 28 transmits the rotating force to the rotating shaft 7, so that the rotating shaft 7 drives the disc 27 to rotate. The rotating disc 27 uses centrifugal force to make the knocking blocks 30 interfere with the internal grit to prevent the grit from caking.

[0060] It should be noted that the knocking block 30 includes two parts. One is a third spring 3001 fixedly connected to the disc 27, and the other is a block 3002 fixedly installed on the third spring 3001. Under the action of centrifugal force, the third spring 3001 is stretched and the block 3002 is thrown out to break up the caked grit.

[0061] Embodiment 3:

[0062] Refer to Figures 1-7 , which is basically the same as Embodiment 2. On the basis of Embodiment 2, the entire technical solution is further optimized.

[0063] Refer to Figure 1 and Figure 2 and Figure 3, in order to leave a spraying distance between the first sand outlet 301 and the fixed wing, the high-temperature alloy casting device for aircraft in this embodiment further includes: an adjusting rod 31 threadedly installed in the anti-slip seat 5, and a roller 33 is fixedly installed at the lower end of the adjusting rod 31; a limiting plate 21 is elastically installed on the adjusting rod 31.

[0064] When sandblasting the groove on the fixed wing, the roller 33 contacts the inner top surface of the groove on the fixed wing, leaving a gap between the sandblasting pipe 1 and the inner bottom surface of the groove, so as to avoid over-sandblasting and damaging the fixed wing itself.

[0065] A high-temperature alloy casting method for aircraft is as follows:

[0066] Step 1: Place the fixed wing in the sandblasting box;

[0067] Step 2: Insert the long sandblasting pipe 1 into the groove;

[0068] Step 3: When the sandblasting work starts, the sand and compressed air are transferred to the mixing chamber 2. The cam 25 on the transmission shaft 17 intermittently presses the driving plate 24, so that the driving plate 24 pushes the piston plate 22 inside the mixing chamber 2 to slide up and down through the connecting column 23. The sliding piston plate 22 provides a preliminary acceleration for the sand, so that the sand and compressed air quickly enter the mixing pipe 4;

[0069] Step 4: During the downward pressing of the piston plate 22, the third gear 28 meshes with the rack 29 and rotates. The rotating third gear 28 transmits the rotating force to the rotating shaft 7, so that the rotating shaft 7 drives the disc 27 to rotate. The rotating disc 27 uses centrifugal force to interfere with the internal sand, avoiding sand caking

[0070] Step 5: The transmission shaft 17 transmits the rotating force to the second gears 19 at both ends. The second gears 19 drive the engaged first gears 14 to rotate. The rotating first gears 14 drive the engaged second gears 19 to rotate. During the rotation of the second gears 19, the first slide plate 8 and the second slide plate 9 drive the upper pressing plate 10 and the lower pressing plate 20 to approach each other to squeeze the airbag 11. The air in the airbag 11 is pressurized and quickly enters the mixing pipe 4 through the air outlet pipe 12, providing an acceleration for the sand in the mixing pipe 4, increasing the flow rate of the sand ejected from the side, and effectively reducing the sandblasting dead angle;

[0071] Step 6: During the extrusion of the airbag 11, the lower pressing plate 20 pushes the limiting plate 21 to move up and down quickly through the resisting rod 26. The limiting plate 21 is located above the second sand outlet 302. When the sand is ejected from the second sand outlet 302, it is blocked by the limiting plate 21, so that all of it acts on the fixed wing, improving the sandblasting efficiency.

[0072] The above are only the preferred specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution and inventive concept of the present invention, making equivalent substitutions or changes, shall be covered by the protection scope of the present invention.

Claims

1. A high-temperature alloy casting device for an aircraft, comprising a sandblasting pipe (1), characterized in that, It further includes: A mixing chamber (2) fixedly installed inside the sandblasting pipe (1). The sand outlet end of the sandblasting pipe (1) is provided with a sand outlet (3), and a mixing pipe (4) is fixedly connected between the sand outlet (3) and the mixing chamber (2); The sand outlet (3) includes a first sand outlet (301) located at the center of the sandblasting pipe (1) and second sand outlets (302) that are symmetric left and right; A non-slip seat (5) fixedly installed on the sandblasting pipe (1). An extrusion part is symmetrically installed inside the non-slip seat (5). A transmission shaft (17) is connected between the two extrusion parts, and the output end of the extrusion part is fixedly connected to the mixing pipe (4) on the second sand outlet (302); A motor (15) is fixedly installed on the sandblasting pipe (1), and the output end of the motor (15) is in transmission connection with the extrusion parts on both sides; The extrusion part includes: a first slide plate (8) and a second slide plate (9) slidably installed inside the non-slip seat (5). An upper pressure plate (10) and a lower pressure plate (20) are respectively fixedly installed on the first slide plate (8) and the second slide plate (9). An airbag (11) is fixedly installed on the lower pressure plate (20), and an air outlet pipe (12) is fixedly connected between the airbag (11) and the mixing pipe (4); A vane (13) is rotatably connected between the first slide plate (8) and the second slide plate (9); A first gear (14) is fixedly installed on the vane (13). One end of the transmission shaft (17) located inside the non-slip seat (5) is fixedly installed with a second gear (19), and the first gear (14) is meshed and connected with the second gear (19); An air inlet pipe (32) is fixedly installed on the airbag (11), and a filter screen (34) and a two-way valve (6) are fixedly installed inside the air inlet pipe (32); The working surface of the air outlet pipe (12) faces the sand outlet (3).

2. The high-temperature alloy casting device for an aircraft according to claim 1, wherein A first bevel gear (16) is fixedly installed at the output end of the motor (15), and a second bevel gear (18) is fixedly installed on the transmission shaft (17). The first bevel gear (16) and the second bevel gear (18) are meshed and connected.

3. A high-temperature alloy casting device for an aircraft according to claim 1, characterized in that, It further includes: A limiting plate (21) slidably installed on the sandblasting pipe (1). A resisting rod (26) that abuts against the limiting plate (21) is fixedly installed on the lower pressure plate (20).

4. The high-temperature alloy casting device for an aircraft according to claim 3, characterized in that, It further includes: A piston plate (22) slidably installed inside the mixing chamber (2). An adapter column (23) is fixedly installed on the piston plate (22), and the upper end of the adapter column (23) penetrates through the mixing chamber (2) and is fixedly installed with a driving plate (24); A cam (25) is fixedly installed on the transmission shaft (17), and the cam (25) is in contact with the driving plate (24).

5. The high-temperature alloy casting device for an aircraft according to claim 4, characterized in that, It further includes: A rotating shaft (7) rotatably installed on the piston plate (22). A disc (27) and a third gear (28) are fixedly installed on the rotating shaft (7), and a rack (29) adapted to the third gear (28) is fixedly installed on the inner wall of the mixing chamber (2); Knocking blocks (30) are uniformly installed on the disc (27) along the circumferential direction.

6. The high-temperature alloy casting device for an aircraft according to claim 5, wherein, It further includes: The adjusting rod (31) is threadedly installed in the anti-slip seat (5), and a roller (33) is fixedly installed at the lower end of the adjusting rod (31); The limiting plate (21) is elastically installed on the adjusting rod (31).

7. A casting method for superalloy used in aircraft, adopting a casting device for superalloy used in aircraft according to any one of claims 1-6, characterized in that, The operation steps are as follows: Step 1: Place the fixed wing in the sandblasting box; Step 2: Perform sandblasting on the surface of the fixed wing; Step 3: Perform sandblasting on the gaps on the fixed wing.

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