A surface coating device for producing aircraft turbine blades

Abstract

The present invention discloses a surface plating device for aircraft turbine blade production, which relates to the field of plating technology. In order to solve the efficiency problem, the device specifically comprises a shell and a shell cover connected to one side of the top of the shell by a hinge, wherein an air jet mechanism is arranged inside the shell cover, and a rotating driving member for fixing and rotating the turbine blade is arranged inside the shell, and a heating coil for heating the turbine blade is fixed on the inner wall of the shell. The present invention sets a boss to horizontally limit the turbine blade, and then cooperates with a ratchet and a mounting base to longitudinally limit the turbine blade, thereby increasing the stability of the limit. At the same time, the limit of the turbine blade by the ratchet is achieved by the rotation of the mounting base, so that the limit can be automatically limited and contact limited, making the installation and removal of the turbine blade more convenient and improving the production efficiency.

Description

Technical Field

[0001] The invention relates to the field of plating technology, in particular to a surface plating device for producing aircraft turbine blades. Background Art

[0002] The working environment of aircraft turbine blades is relatively harsh. In order to increase their service life and performance, a protective layer is coated on the surface of the blades to increase their smoothness and corrosion resistance. In the existing technology, chemical vapor deposition is widely used for surface coating.

[0003] After searching, the Chinese patent publication number CN103374712B discloses a chemical vapor deposition device with a heat shield, comprising a reaction chamber and a susceptor, wherein the susceptor is supported in the reaction chamber by a susceptor support shaft, and the chemical vapor deposition device comprises: a heat shield, wherein the heat shield is used to block radiant heat radiated from a part below the susceptor or from the susceptor support shaft, wherein the heat shield comprises a cylindrical first shield plate and a second shield plate connected to the first shield plate, wherein the second shield plate is arranged below the susceptor and is open at the central part of the second shield plate; and an auxiliary shield, wherein the auxiliary shield is arranged below the first shield in a manner spaced apart from the first shield, and wherein the auxiliary shield blocks heat radiated from the central part of the susceptor toward the bottom of the reaction chamber.

[0004] The above patent has the following shortcomings: it cannot realize the quick installation and disassembly of the blade and the base, so the efficiency is low for batch plating.

[0005] To this end, the present invention provides a surface coating device for producing aircraft turbine blades. Summary of the invention

[0006] The purpose of the present invention is to solve the shortcomings of the prior art and to propose a surface coating device for producing aircraft turbine blades.

[0007] In order to achieve the above object, the present invention adopts the following technical solutions:

[0008] A surface coating device for producing aircraft turbine blades comprises a shell and a shell cover connected to one side of the top of the shell by a hinge.

[0009] The shell cover is provided with an air injection mechanism inside, the shell is provided with a rotary driving member for fixing and rotating the turbine blades inside, and a heating coil for heating the turbine blades is fixed on the inner wall of the shell;

[0010] The rotary drive member comprises a rotor core, the inner wall of the rotor core is rotatably connected to a mounting base via a rotating shaft, the bottom of the rotating shaft is connected to a motor via a crankshaft, and the motor is fixed to the bottom inner wall of the housing via bolts;

[0011] The top of the mounting base is provided with a plurality of bosses corresponding to the mounting flange holes of the turbine blades, and the inner wall of the bosses is provided with automatic locking parts;

[0012] The automatic locking component includes a centrifugal block and a slide, the boss is radially slidably connected with a pawl, an elastic rod is fixed on the opposite side of the pawl, the slide and the pawl cooperate through an inclined surface, and the centrifugal block is slidably connected to the radial direction of the mounting base, a connecting rope is fixed on the top of the centrifugal block, the other end of the connecting rope is fixed to the side wall of the slide, the bottom outer wall of the slide is buckled with a spring 1, and the other end of the spring 1 is buckled to the outer wall of the mounting base.

[0013] Preferably: the jet mechanism includes an inner cover, and a through cavity is formed between the inner cover and the shell cover, one side of the through cavity is welded and connected to an air inlet, the inner wall of the inner cover is provided with a radial air outlet groove, and the side wall of the shell cover is slidably connected to a sealing plate for sealing the air outlet groove.

[0014] Furthermore: the width of the air outlet groove increases gradually along the inner circumference of the inner cover toward the outer circumference.

[0015] Based on the above scheme: the top outer wall of the shell cover is slidably connected to a lifting plate through a "T"-shaped guide rod, the side wall of the shell cover is rotatably connected to a plurality of gears meshing with the blocking plate, and the bottom outer wall of the lifting plate is fixed with a plurality of racks meshing with the gears.

[0016] A better solution among the above solutions is: the lifting plate and the opposite side of the shell cover are buckled with the same spring 2, and the bottom outer wall of the lifting plate is fixed with a permanent magnet by bolts, and the top outer wall of the shell cover is fixed with an electromagnet arranged opposite to the permanent magnet, and the electromagnet and the permanent magnet have the same magnetic pole on the opposite side.

[0017] As a further solution of the present invention: the outer wall of the rotating shaft is fixed with a rotor core by bolts, the bottom outer wall of the support frame is fixed with a stator winding used in conjunction with the rotor core, and the stator winding is a power supply for the heating coil and the electromagnet.

[0018] At the same time, a dual-function fluid drive mechanism is arranged inside the shell, and the dual-function fluid drive mechanism includes a connecting rod rotatably connected to the outer wall of the crankshaft and a piston rod rotatably connected to the other end of the connecting rod, and the other end of the piston rod is fixed with a piston by bolts, and the outer wall of the piston is slidably connected with a cylinder body, and the cylinder body is fixed to the inner wall of the shell.

[0019] As a preferred embodiment of the present invention: two air ports 1 are provided at one end of the cylinder body, and a group of simple one-way components are respectively arranged inside the two air ports 1, and the passage directions of the two groups of simple one-way components are different, one of which is connected to the inner cavity of the shell from the outside of the cylinder body to the air port 1 inside the cylinder body, and the other air port 1 is connected to the air storage tank through a connecting pipe.

[0020] At the same time, two air ports 2 are provided at the other end of the cylinder body, and a group of simple one-way components are respectively arranged inside the two air ports 2, and the passage directions of the two groups of simple one-way components are different. One of the passage directions is from the outside of the cylinder body to the inside of the cylinder body, and the air port 2 is connected to the gaseous precursor material supply part, and the other air port 2 is connected to the air inlet.

[0021] As a better solution of the present invention: the connecting rope includes a hollow plate and a plurality of fan-shaped rubber sheets that fit each other, the hollow plate is fixed to the inner walls of air port one and air port two, the outer circumference of the hollow plate is bonded to the end face of the hollow plate, and the plurality of fan-shaped rubber sheets can form a complete circular plane.

[0022] The beneficial effects of the present invention are:

[0023] 1. The turbine blades are horizontally limited by setting a boss, and the turbine blades are longitudinally limited by the ratchet and the mounting base, thereby increasing the stability of the limit. At the same time, the limit of the turbine blades by the ratchet is achieved by the rotation of the mounting base, so that automatic limit and contact limit can be achieved, making the installation and disassembly of the turbine blades more convenient and improving production efficiency.

[0024] 2. By setting the blocking plate, the position of the blocking plate can be utilized to achieve different blocking positions of the blocking plate on the air outlet slot, so as to adapt to blades of different diameters. At the same time, by setting the shape of the air outlet slot, the opening of the air outlet slot on the relatively outer side can be made larger, thereby ensuring the uniformity of plating.

[0025] 3. By setting the stator winding and the rotor core, utilizing the relationship between the motor speed and torque, and combining the characteristics of the aircraft turbine blade's own weight and size, the automatic adjustment of the outlet slot spray radius can be achieved. At the same time, the heating power of the heating coil can be matched with the heat dissipation rate of the turbine blade to ensure that the temperature of the turbine blade is appropriate. At the same time, the entire process does not require manual or algorithm intervention control, which increases synchronous linkage.

[0026] 4. By setting up components such as gas port 1, piston, cylinder body, gas port 2, on the one hand, the linkage between gas drive and the rotation drive of turbine blades can be realized, so as to realize synchronous opening and closing and simplify the control logic. On the other hand, the air intake and air outlet of the inner cavity of the shell can be matched with each other to ensure the air pressure balance under long-term plating. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the overall structure of a surface coating device for producing aircraft turbine blades proposed by the present invention;

[0028] Figure 2 This is a schematic diagram of the structure of a rotating drive component of a surface coating device for producing aircraft turbine blades proposed by the present invention;

[0029] Figure 3 This is a schematic diagram of the structure of a mounting base of a surface coating device for producing aircraft turbine blades proposed by the present invention;

[0030] Figure 4 The present invention provides a surface coating device for producing aircraft turbine blades. Figure 3 The enlarged structural diagram of part A in the middle;

[0031] Figure 5 This is a schematic diagram of the jet mechanism structure of a surface coating device for producing aircraft turbine blades proposed by the present invention;

[0032] Figure 6 This is a schematic diagram of the structure of a "T"-shaped guide rod, permanent magnet, spring 2, lifting plate, rack and gear of a surface plating device for aircraft turbine blade production proposed by the present invention;

[0033] Figure 7 This is a schematic diagram of the structure of a dual-function fluid drive mechanism of a surface coating device for aircraft turbine blade production proposed by the present invention;

[0034] Figure 8 The present invention is a schematic diagram of a simple one-way component structure of a surface coating device for producing aircraft turbine blades.

[0035] In the figure: 1, housing; 2, turbine blades; 3, rotating drive member; 4, heating coil; 5, hinge; 6, housing cover; 7, jet mechanism; 8, dual-function fluid drive mechanism; 9, rotating shaft; 10, stator winding; 11, mounting base; 12, rotor core; 13, support frame; 14, crankshaft; 15, boss; 16, automatic locking member; 17, centrifugal block; 18, connecting rope; 19, spring 1; 20, ratchet; 21, slide; 22, inner cover; 23, air outlet Groove; 24, blocking plate; 25, through cavity; 26, air inlet; 27, electromagnet; 28, "T"-shaped guide rod; 29, permanent magnet; 30, spring 2; 31, lifting plate; 32, rack; 33, gear; 34, air port 1; 35, piston; 36, cylinder body; 37, air port 2; 38, simple one-way component; 39, connecting pipe; 40, piston rod; 41, connecting rod; 42, fan-shaped rubber sheet; 43, hollow plate; 44, motor; 45, elastic rod. DETAILED DESCRIPTION

[0036] The technical solution of the present invention is further described in detail below in conjunction with specific implementation methods.

[0037] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0038] Embodiment 1:

[0039] A surface coating device for producing aircraft turbine blades, such as Figure 1-Figure 8 As shown, it includes a housing 1 and a housing cover 6 connected to one side of the top of the housing 1 through a hinge 5, and the other side of the housing 1 and the housing cover 6 can be locked together through a snap-fit.

[0040] An injection mechanism 7 is disposed inside the shell cover 6 , a rotation drive member 3 for fixing and rotationally driving the turbine blades 2 is disposed inside the shell 1 , and a heating coil 4 for heating the turbine blades 2 is fixed to the inner wall of the shell 1 .

[0041] The rotary drive member 3 includes a rotor core 12 , the inner wall of the rotor core 12 is rotatably connected to a mounting base 11 via a rotating shaft 9 , the bottom of the rotating shaft 9 is connected to a motor 44 via a crankshaft 14 , and the motor 44 is fixed to the bottom inner wall of the housing 1 via bolts.

[0042] A plurality of bosses 15 corresponding to the mounting flange holes of the turbine blades 2 are arranged on the top of the mounting base 11 , and automatic locking members 16 are arranged on the inner walls of the bosses 15 .

[0043] The automatic locking member 16 includes a centrifugal block 17 and a slide 21, the boss 15 is radially slidably connected with a pawl 20, and an elastic rod 45 is fixed on the opposite side of the pawl 20, the slide 21 and the pawl 20 cooperate with each other through an inclined surface, and the centrifugal block 17 is slidably connected to the radial direction of the mounting base 11, a connecting rope 18 is fixed to the top of the centrifugal block 17, and the other end of the connecting rope 18 is fixed to the side wall of the slide 21, and a spring 19 is buckled on the bottom outer wall of the slide 21, and the other end of the spring 19 is buckled on the outer wall of the mounting base 11.

[0044] When the device is in use, the flange hole of the turbine blade 2 and the boss 15 can be inserted backward, and then the motor 44 is started. The motor 44 drives the mounting base 11 and the turbine blade 2 to rotate, and the heating coil 4 is started at the same time, which can generate an alternating magnetic field, thereby generating eddy currents in the turbine blade 2. In order to prevent the remaining components from being heated, they can be made of insulating materials. The eddy currents generated in the turbine blade 2 generate Joule heat to heat the turbine blade 2, and at the same time, a gaseous precursor substance can be sprayed out of the jet mechanism 7. After the surface of the turbine blade 2 is released, a chemical reaction occurs to form a deposition layer, and finally a protective film is formed. At the same time, when the mounting base 11 rotates, the centrifugal block 17 will be moved outward by the centrifugal force. At this time, the slide 21 is pulled downward by the connecting rope 18, so that the pawl 20 is moved outward by the inclined surface cooperation, and the turbine blade 2 is longitudinally limited.

[0045] This device, by setting a boss 15 to limit the turbine blade 2 horizontally, and then cooperating with the pawl 20 and the mounting base 11 to limit the turbine blade 2 longitudinally, thereby increasing the stability of the limitation. At the same time, the limitation of the turbine blade 2 by the pawl 20 is achieved by the rotation of the mounting base 11, so that automatic limitation and contact limitation can be achieved, making the installation and disassembly of the turbine blade 2 more convenient and increasing production efficiency.

[0046] To solve the jet problem; Figure 5 , 6 As shown in Figure 7, the jet mechanism 7 includes an inner cover 22, and a through cavity 25 is formed between the inner cover 22 and the shell cover 6. One side of the through cavity 25 is welded and connected to an air inlet 26. The inner wall of the inner cover 22 is provided with a radial air outlet groove 23, and the side wall of the shell cover 6 is slidably connected with a sealing plate 24 for sealing the air outlet groove 23.

[0047] The width of the air outlet groove 23 increases gradually from the inner circumference to the outer circumference of the inner cover 22 .

[0048] The gaseous precursor material can be introduced into the air inlet 26 and then sprayed out through the air outlet slot 23. The position of the blocking plate 24 can be adjusted to achieve different blocking positions of the blocking plate 24 on the air outlet slot 23, so as to adapt to blades of different diameters.

[0049] By setting the sealing plate 24, the present device can utilize the position of the sealing plate 24 to achieve different sealing positions of the sealing plate 24 on the air outlet groove 23, so as to adapt to blades of different diameters. At the same time, by setting the shape of the air outlet groove 23, the opening of the air outlet groove 23 on the relatively outer side can be made larger, thereby ensuring the uniformity of plating.

[0050] The top outer wall of the shell cover 6 is slidably connected to a lifting plate 31 through a "T"-shaped guide rod 28, and the side wall of the shell cover 6 is rotatably connected to a plurality of gears 33 meshing with the blocking plate 24, and the bottom outer wall of the lifting plate 31 is fixed with a plurality of racks 32 meshing with the gears 33.

[0051] The lifting plate 31 is buckled with the same spring 2 30 on the opposite side of the shell cover 6, and the bottom outer wall of the lifting plate 31 is fixed with a permanent magnet 29 by bolts, and the top outer wall of the shell cover 6 is fixed with an electromagnet 27 arranged opposite to the permanent magnet 29, and the electromagnet 27 has the same magnetic pole as the permanent magnet 29 on the opposite side.

[0052] When the voltage applied to the electromagnet 27 is adjusted, the field strength of the electromagnet 27 changes, so that the magnetic repulsion between the electromagnet 27 and the permanent magnet 29 changes, so that the lifting plate 31 moves, thereby driving the rack 32 to move, and then driving the blocking plate 24 to move through the gear 33.

[0053] In order to solve the adaptive control problem; such as Figure 2 As shown, the outer wall of the rotating shaft 9 is fixed with a rotor core 12 by bolts, and the bottom outer wall of the support frame 13 is fixed with a stator winding 10 used in conjunction with the rotor core 12, and the stator winding 10 is the power supply for the heating coil 4 and the electromagnet 27.

[0054] Since the appearance of aircraft turbine blades is basically similar, the difference is that the blade diameters of engines of different sizes are different, which leads to different deadweights. At the same time, when the input power of the motor 44 remains unchanged, the output torque of the motor 44 is inversely proportional to the speed, that is, P=F*V, where P is power, F is output torque, and V is speed. Based on this:

[0055] When the diameter of the blade is large, the deadweight is large, and the load of the motor 44 is large, so that the rotation speed is reduced, resulting in a small relative rotation speed between the rotor core 12 and the stator winding 10. The induced electromotive force generated in the stator winding 10 reduces the input voltage of the electromagnet 27 on the one hand, and the input voltage of the heating coil 4 on the other hand:

[0056] ①: When the input voltage of the electromagnet 27 decreases, the magnetic repulsion between the electromagnet 27 and the permanent magnet 29 decreases, so that the lifting plate 31 moves downward, the blocking plate 24 moves outward, and the jet range of the gas outlet slot 23 increases;

[0057] ②: When the input voltage of the heating coil 4 is reduced, its heating power for the turbine blade 2 is reduced. Since the turbine blade 2 is in a low speed state at this time, its relative movement with the gas is small, and the heat transfer loss is small. Therefore, the low heating power corresponds to the small heat loss, maintaining the temperature of the entire turbine blade 2 at a suitable level.

[0058] The device, by setting the stator winding 10 and the rotor core 12, utilizes the relationship between the rotation speed and torque of the motor 44, combined with the characteristics of the deadweight and size of the aircraft turbine blades, so as to realize the automatic adjustment of the spray radius of the air outlet slot 23 and at the same time make the heating power of the heating coil 4 match the heat dissipation rate of the turbine blade 2, thereby ensuring that the temperature of the turbine blade 2 is appropriate. At the same time, the entire process does not require manual or algorithm intervention control, which increases the synchronization linkage.

[0059] When the present embodiment is in use, the flange hole of the turbine blade 2 and the boss 15 can be inserted into the rear, and then the motor 44 is started, and the motor 44 drives the mounting base 11 and the turbine blade 2 to rotate, and at the same time the heating coil 4 is started, which can generate an alternating magnetic field, thereby generating eddy currents in the turbine blade 2. In order to prevent the remaining components from being heated, the insulating material can be used. The eddy currents generated in the turbine blade 2 generate Joule heat to heat the turbine blade 2, and at the same time, the gaseous precursor material can be ejected from the jet mechanism 7, which releases the surface of the turbine blade 2, generates a chemical reaction to form a deposition layer, and finally forms a protective film, and at the same time the mounting base 11 is started. When the platform 11 rotates, the centrifugal block 17 will move outward under the action of centrifugal force. At this time, the slide 21 is pulled downward by the connecting rope 18, so that the ratchet 20 is moved outward by the inclined surface cooperation, and the turbine blade 2 is longitudinally limited. When the voltage passed into the electromagnet 27 is adjusted, the field strength of the electromagnet 27 changes, so that the magnetic repulsion between the electromagnet 27 and the permanent magnet 29 changes, so that the lifting plate 31 moves, thereby driving the rack 32 to move, and then driving the blocking plate 24 to move through the gear 33, so that the blocking plate 24 can block the outlet groove 23 at different positions, so as to adapt to different vertical The blades have different diameters, and since the appearances of aircraft turbine blades are basically similar, the difference is that the blade diameters of engines of different sizes are different, resulting in different deadweights. At the same time, when the input power of the motor 44 remains unchanged, the output torque of the motor 44 is inversely proportional to the speed, that is, P=F*V, where P is power, F is output torque, and V is speed. Based on this: when the diameter of the blade is larger, the deadweight is larger, and the load of the motor 44 is larger, thereby reducing the speed, resulting in a smaller relative speed between the rotor core 12 and the stator winding 10, and the induced electromotive force generated in the stator winding 10, thereby generating a large amount of electromagnetic force. 7, on the other hand, the input voltage of the heating coil 4 is reduced: ①: when the input voltage of the electromagnet 27 is reduced, the magnetic repulsion between the electromagnet 27 and the permanent magnet 29 is reduced, so that the lifting plate 31 moves downward, the sealing plate 24 moves outward, and the jet range of the air outlet slot 23 increases; ②: when the input voltage of the heating coil 4 is reduced, its heating power for the turbine blade 2 is reduced. Since the turbine blade 2 is in a low speed state at this time, its relative motion with the gas is small, and the heat transfer loss is small, so that the low heating power corresponds to the small heat loss, maintaining the appropriate temperature of the entire turbine blade 2.

[0060] Embodiment 2:

[0061] A surface coating device for producing aircraft turbine blades, such as Figure 7 , 8 As shown, in order to solve the problem of air supply and exhaust, this embodiment makes the following improvements on the basis of embodiment 1: a dual-function fluid drive mechanism 8 is arranged inside the shell 1, and the dual-function fluid drive mechanism 8 includes a connecting rod 41 rotatably connected to the outer wall of the crankshaft 14 and a piston rod 40 rotatably connected to the other end of the connecting rod 41, and the other end of the piston rod 40 is fixed with a piston 35 by bolts, and the outer wall of the piston 35 is slidably connected with a cylinder body 36, and the cylinder body 36 is fixed to the inner wall of the shell 1.

[0062] One end of the cylinder body 36 is provided with two air ports 34, and a group of simple one-way components 38 are respectively arranged inside the two air ports 34, and the passage directions of the two groups of simple one-way components 38 are different. One of the passage directions is from the outside of the cylinder body 36 to the inside of the cylinder body 36, and the air port 34 is connected to the inner cavity of the shell 1, and the other air port 34 is connected to the air storage tank through a connecting pipe 39.

[0063] Two air ports 37 are provided at the other end of the cylinder body 36, and a group of simple one-way components 38 are respectively arranged inside the two air ports 37, and the passage directions of the two groups of simple one-way components 38 are different. One of the passage directions is from the outside of the cylinder body 36 to the inside of the cylinder body 36, and the air port 37 is connected to the gaseous precursor material supply part, and the other air port 37 is connected to the air inlet 26.

[0064] The connecting rope 18 includes a hollow plate 43 and a plurality of fan-shaped rubber sheets 42 that fit each other. The hollow plate 43 is fixed to the inner walls of the air port 1 34 and the air port 2 37 . The outer circumference of the hollow plate 43 is bonded to the end surface of the hollow plate 43 , and the plurality of fan-shaped rubber sheets 42 can form a complete circular plane.

[0065] When this embodiment is in use, when the crankshaft 14 rotates, it can drive the piston rod 40 to reciprocate through the connecting rod 41, so that the piston 35 reciprocates relative to the cylinder body 36. When the cylinder body 36 reciprocates, on the one hand, it can suck in the gaseous precursor material in the gaseous precursor material supply part through the gas port 2 37 and then transport it to the air inlet 26. On the other hand, it can also suck in the gaseous material in the casing 1 that passes over the turbine blades 2 and then store it in the gas storage tank for recovery.

[0066] This device, by providing components such as air port 1 34, piston 35, cylinder body 36, air port 2 37, can, on the one hand, realize the linkage between the gas drive and the rotation drive of the turbine blade 2, thereby realizing synchronous opening and closing and simplifying the control logic; on the other hand, it can also make the air intake and air outlet of the inner cavity of the shell 1 match each other, ensuring the air pressure balance under long-term plating.

[0067] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A surface coating device for producing aircraft turbine blades, comprising a housing (1) and a housing cover (6) connected to one side of the top of the housing (1) via a hinge (5), characterized in that: An air injection mechanism (7) is disposed inside the shell cover (6), a rotary drive member (3) for fixing and rotationally driving the turbine blades (2) is disposed inside the shell (1), and a heating coil (4) for heating the turbine blades (2) is fixed on the inner wall of the shell (1); The rotary drive member (3) comprises a rotor core (12), the inner wall of the rotor core (12) being rotatably connected to a mounting base (11) via a rotating shaft (9), the bottom of the rotating shaft (9) being connected to an electric motor (44) via a crankshaft (14), and the electric motor (44) being fixed to the bottom inner wall of the housing (1) via bolts; A plurality of bosses (15) corresponding to the mounting flange holes of the turbine blades (2) are arranged on the top of the mounting base (11), and an automatic locking member (16) is arranged on the inner wall of the boss (15); The automatic locking member (16) comprises a centrifugal block (17) and a slide (21); the boss (15) is radially slidably connected with a pawl (20); an elastic rod (45) is fixed on the opposite side of the pawl (20); the slide (21) and the pawl (20) cooperate with each other via an inclined surface; the centrifugal block (17) is slidably connected to the radial direction of the mounting base (11); a connecting rope (18) is fixed to the top of the centrifugal block (17); the other end of the connecting rope (18) is fixed to the side wall of the slide (21); a spring 1 (19) is buckled to the outer wall of the bottom of the slide (21); the other end of the spring 1 (19) is buckled to the outer wall of the mounting base (11).

2. A surface coating device for producing aircraft turbine blades according to claim 1, characterized in that: The jet mechanism (7) comprises an inner cover (22), and a through cavity (25) is formed between the inner cover (22) and the shell cover (6), one side of the through cavity (25) is welded and connected to an air inlet (26), an inner wall of the inner cover (22) is provided with a radial air outlet groove (23), and a side wall of the shell cover (6) is slidably connected to a blocking plate (24) for blocking the air outlet groove (23).

3. A surface coating device for producing aircraft turbine blades according to claim 2, characterized in that: The width of the air outlet groove (23) increases gradually from the inner circumference to the outer circumference of the inner cover (22).

4. A surface coating device for producing aircraft turbine blades according to claim 2, characterized in that: The top outer wall of the shell cover (6) is slidably connected to a lifting plate (31) via a "T"-shaped guide rod (28); the side wall of the shell cover (6) is rotatably connected to a plurality of gears (33) meshing with the blocking plate (24); and the bottom outer wall of the lifting plate (31) is fixed with a plurality of racks (32) meshing with the gears (33).

5. A surface coating device for producing aircraft turbine blades according to claim 4, characterized in that: The lifting plate (31) and the shell cover (6) are buckled with a same spring 2 (30) on the opposite side thereof, and a permanent magnet (29) is fixed to the bottom outer wall of the lifting plate (31) by bolts, and an electromagnet (27) arranged opposite to the permanent magnet (29) is fixed to the top outer wall of the shell cover (6), and the electromagnet (27) and the permanent magnet (29) have the same magnetic pole on the opposite side thereof.

6. A surface coating device for producing aircraft turbine blades according to claim 5, characterized in that: A rotor core (12) is fixed to the outer wall of the rotating shaft (9) by means of bolts, and a stator winding (10) used in conjunction with the rotor core (12) is fixed to the bottom outer wall of the support frame (13), and the stator winding (10) is a power supply for the heating coil (4) and the electromagnet (27).

7. A surface coating device for producing aircraft turbine blades according to claim 1, characterized in that: A dual-function fluid drive mechanism (8) is arranged inside the housing (1), and the dual-function fluid drive mechanism (8) comprises a connecting rod (41) rotatably connected to the outer wall of the crankshaft (14) and a piston rod (40) rotatably connected to the other end of the connecting rod (41); a piston (35) is fixed to the other end of the piston rod (40) by bolts; the outer wall of the piston (35) is slidably connected to a cylinder body (36); and the cylinder body (36) is fixed to the inner wall of the housing (1).

8. A surface coating device for producing aircraft turbine blades according to claim 7, characterized in that: One end of the cylinder body (36) is provided with two air ports (34), each of which has a set of simple one-way components (38) disposed therein. The two sets of simple one-way components (38) have different passage directions, one of which is in the direction of the air port (34) from the outside of the cylinder body (36) to the inside of the cylinder body (36) and connected to the inner cavity of the housing (1), and the other air port (34) is connected to an air storage tank via a connecting pipe (39).

9. A surface coating device for producing aircraft turbine blades according to claim 8, characterized in that: The other end of the cylinder body (36) is provided with two gas ports (37), each of which is provided with a set of simple one-way components (38). The passage directions of the two sets of simple one-way components (38) are different. One of the gas ports (37) with a passage direction from the outside of the cylinder body (36) to the inside of the cylinder body (36) is connected to a gaseous precursor material supply portion, and the other gas port (37) is connected to an air inlet (26).

10. A surface coating device for producing aircraft turbine blades according to claim 9, characterized in that: The connecting rope (18) comprises a hollow plate (43) and a plurality of fan-shaped rubber sheets (42) which fit each other, the hollow plate (43) being fixed to the inner walls of the first air port (34) and the second air port (37), the outer circumference of the hollow plate (43) being bonded to the end surface of the hollow plate (43), and the plurality of fan-shaped rubber sheets (42) can form a complete circular plane.

Images