CN114939485A - Coating device for surface treatment of aircraft parts and coating method thereof - Google Patents
Coating device for surface treatment of aircraft parts and coating method thereof Download PDFInfo
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- CN114939485A CN114939485A CN202210886479.8A CN202210886479A CN114939485A CN 114939485 A CN114939485 A CN 114939485A CN 202210886479 A CN202210886479 A CN 202210886479A CN 114939485 A CN114939485 A CN 114939485A
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- turbine blade
- fixed
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- spraying
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B5/00—Electrostatic spraying apparatus; Spraying apparatus with means for charging the spray electrically; Apparatus for spraying liquids or other fluent materials by other electric means
- B05B5/06—Electrostatic spraying apparatus; Spraying apparatus with means for charging the spray electrically; Apparatus for spraying liquids or other fluent materials by other electric means using electric arc
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B12/00—Arrangements for controlling delivery; Arrangements for controlling the spray area
- B05B12/08—Arrangements for controlling delivery; Arrangements for controlling the spray area responsive to condition of liquid or other fluent material to be discharged, of ambient medium or of target ; responsive to condition of spray devices or of supply means, e.g. pipes, pumps or their drive means
- B05B12/12—Arrangements for controlling delivery; Arrangements for controlling the spray area responsive to condition of liquid or other fluent material to be discharged, of ambient medium or of target ; responsive to condition of spray devices or of supply means, e.g. pipes, pumps or their drive means responsive to conditions of ambient medium or target, e.g. humidity, temperature position or movement of the target relative to the spray apparatus
- B05B12/124—Arrangements for controlling delivery; Arrangements for controlling the spray area responsive to condition of liquid or other fluent material to be discharged, of ambient medium or of target ; responsive to condition of spray devices or of supply means, e.g. pipes, pumps or their drive means responsive to conditions of ambient medium or target, e.g. humidity, temperature position or movement of the target relative to the spray apparatus responsive to distance between spray apparatus and target
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B12/00—Arrangements for controlling delivery; Arrangements for controlling the spray area
- B05B12/16—Arrangements for controlling delivery; Arrangements for controlling the spray area for controlling the spray area
- B05B12/20—Masking elements, i.e. elements defining uncoated areas on an object to be coated
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B13/00—Machines or plants for applying liquids or other fluent materials to surfaces of objects or other work by spraying, not covered by groups B05B1/00 - B05B11/00
- B05B13/02—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work
- B05B13/0221—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work characterised by the means for moving or conveying the objects or other work, e.g. conveyor belts
- B05B13/0228—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work characterised by the means for moving or conveying the objects or other work, e.g. conveyor belts the movement of the objects being rotative
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B13/00—Machines or plants for applying liquids or other fluent materials to surfaces of objects or other work by spraying, not covered by groups B05B1/00 - B05B11/00
- B05B13/02—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work
- B05B13/0221—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work characterised by the means for moving or conveying the objects or other work, e.g. conveyor belts
- B05B13/0271—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work characterised by the means for moving or conveying the objects or other work, e.g. conveyor belts the object or work standing still during the spraying operation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B13/00—Machines or plants for applying liquids or other fluent materials to surfaces of objects or other work by spraying, not covered by groups B05B1/00 - B05B11/00
- B05B13/02—Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work
- B05B13/0278—Arrangement or mounting of spray heads
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
- B05B15/00—Details of spraying plant or spraying apparatus not otherwise provided for; Accessories
- B05B15/60—Arrangements for mounting, supporting or holding spraying apparatus
- B05B15/68—Arrangements for adjusting the position of spray heads
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/10—Greenhouse gas [GHG] capture, material saving, heat recovery or other energy efficient measures, e.g. motor control, characterised by manufacturing processes, e.g. for rolling metal or metal working
Landscapes
- Spray Control Apparatus (AREA)
Abstract
The invention relates to the technical field of part coating, in particular to a coating device for surface treatment of airplane parts and a coating method thereof, wherein the coating device comprises a supporting table, two belt pulleys are rotationally connected to the top surface of the supporting table, two conveying belts are jointly connected to the two belt pulleys in a transmission manner, a first motor is fixed on the inner top surface of the supporting table, and an output shaft of the first motor penetrates through the top surface of the supporting table and is coaxially fixed with one belt pulley; a plurality of positioning plates are arranged between the two conveying belts, the upper ends and the lower ends of the positioning plates are respectively fixed on the corresponding conveying belts, the middle parts of the positioning plates are rotatably connected with rotating shafts, and one ends of the rotating shafts are fixedly provided with supporting blocks; in the process of rotating and turning over the turbine blade, the nozzle position is readjusted by the coating mechanism, so that the same spraying distance is continuously maintained after the turbine blade is turned over, and the problem of reduction of the bonding strength and hardness of the coating due to different spraying distances is further solved.
Description
Technical Field
The invention relates to the field of part coating, in particular to a coating device for surface treatment of aircraft parts and a coating method thereof.
Background
With the development of the aerospace industry, the performance requirements on the engine are higher and higher, and the engine has high thrust-weight ratio and large thrust force, the adopted main measure is to increase the temperature of the inlet of the turbine, so that engine parts have higher levels of thermal shock resistance, high-temperature corrosion resistance, heat alternation resistance and complex stress, and for a carrier-based aircraft, the blades of the engine are required to have higher corrosion resistance due to long-term service in an ocean high-salt fog environment; in an airplane flying in desert, blades of an engine have better abrasion resistance.
The prior art discloses a part of invention patents related to coating of airplane parts, namely a Chinese patent with the application number of 202020677994.1, discloses a spraying mechanism for airplane parts, and belongs to the field of airplane part machining equipment. Comprises a spraying main body and a spraying pipe; a spraying pipe is arranged on the left side of the spraying main body, and a power supply, a metal wire, a wire feeding roller, a conductive block, a conductive nozzle and an air nozzle are arranged in the spraying main body; the spraying mechanism for the aircraft parts further comprises a protection device and an adjusting device; the protective device is in sliding fit with the spraying pipe; the adjusting device is fixedly connected to the spraying pipe, and the adjusting device is located inside the protective device.
In order to enable the turbine blade of an engine to have the levels of thermal shock resistance, high-temperature corrosion resistance, heat alternation resistance and complex stress, a metal coating needs to be coated on the turbine blade, most of the existing coating methods are arc spraying methods, the metal coating is coated on the turbine blade, the distance between a spraying opening and a spraying surface is different in the arc spraying process, the bonding strength and the hardness of the coating can be influenced, but the outer wall of the turbine blade is arc-shaped, so that when the turbine blade is simply sprayed by a single arc spraying gun, the distance between the spraying opening and the spraying surface is difficult to maintain the same, and the coating is uneven.
Disclosure of Invention
The invention aims to solve the defects in the prior art and provides a coating device for treating the surface of an aircraft part and a coating method thereof.
In order to achieve the above purposes, the technical scheme adopted by the invention is as follows: a coating device for surface treatment of airplane parts comprises a supporting table, wherein four belt pulleys are rotatably connected to the top surface of the supporting table, every two of the four belt pulleys are coaxially fixed, two belt pulleys at the same height are jointly connected with a conveying belt in a transmission mode, a first motor is fixed to the inner top surface of the supporting table, and an output shaft of the first motor penetrates through the top surface of the supporting table and then is coaxially fixed to one of the belt pulleys;
a plurality of positioning plates are arranged between the two conveying belts, the upper ends and the lower ends of the positioning plates are respectively fixed on the corresponding conveying belts, the middle parts of the positioning plates are rotatably connected with rotating shafts, supporting blocks are fixed at one ends of the rotating shafts, positioning grooves are formed in the supporting blocks and are matched with the turbine blades;
the top surface of the supporting table is fixedly communicated with a spraying box, the top surface of the spraying box is provided with a clamping and turning-over mechanism, and the clamping and turning-over mechanism is used for driving the turning-over of the turbine blade;
and when the turbine blade is turned over, the coating mechanism can adjust the position of a nozzle for spraying the metal coating to be matched with the corresponding curved surface on the turbine blade.
Preferably, centre gripping turn-over mechanism includes the riser, the riser is fixed on the outer wall of spraying case, one side of riser is rotated and is connected with the rolling disc, one side that the rolling disc kept away from the riser is fixed with electric putter, electric putter's piston rod end is fixed with the top and moves the dish, the opposite side of riser is fixed with the second motor, the output shaft of second motor runs through behind the riser fixed mutually with the rolling disc.
Preferably, the coating mechanism comprises a strip-shaped through hole, the strip-shaped through hole is formed in the top surface of the spraying box, a sliding plate is connected to the inside of the strip-shaped through hole in a sliding manner, three mounting holes are formed in the sliding plate, arc spray heads are arranged below the three mounting holes, the bottom of each arc spray head is connected with a wire feeder, a control system, a power supply and a compressed air supply system which are arranged outside the arc spray heads through pipelines, discharge pipes of the arc spray heads penetrate through the corresponding mounting holes and extend out, first springs are jointly fixed between the arc spray heads and the sliding plate on two sides, the first springs are sleeved on the outer sides of the discharge pipes, a driving plate is fixed on the bottom surface of the sliding plate, a reciprocating driving mechanism is arranged on one side of the driving plate and used for driving the driving plate to reciprocate along the strip-shaped through hole, and a support bar is connected to the bottom of each arc spray head in a sliding manner, middle part the support bar highly be higher than the support bar of both sides, all seted up the through wires groove on the top surface of support bar, it is three the both ends of support bar all are provided with relative displacement mechanism, the middle part the support bar top is provided with pushing mechanism, rotates the in-process of turn-over at turbine blade, pushing mechanism promotes the support bar at middle part downwards, when the support bar downstream at middle part, relative displacement mechanism adjusts the support bar of both sides and rises.
Preferably, reciprocal actuating mechanism includes two location strips, the location strip sets up the both ends at the bar through-hole respectively, the location strip is all fixed on the interior top surface of spraying case, two be provided with reciprocal lead screw and gag lever post between the location strip jointly, the both ends of reciprocal lead screw are all rotated and are connected on the location strip, the both ends of gag lever post are all fixed on the location strip, reciprocal lead screw and drive plate threaded connection, gag lever post and drive plate sliding connection, one side of location strip is fixed with the third motor, the output shaft of third motor is fixed mutually with reciprocal lead screw after running through the location strip.
Preferably, relative displacement mechanism includes two first gears, two first gear is located respectively between two adjacent support bars, every the both sides of first gear all are provided with first rack and second rack, two the second rack is fixed respectively on the support bar lateral wall of both sides, two first rack is all fixed on the support bar lateral wall at middle part, two first gear all rotates to be connected on the location strip, first gear meshes with adjacent first rack and second rack simultaneously.
Preferably, pushing mechanism is including the groove of stepping down, U template, two cams, two the outside at top movable disk and supporting shoe is established to the cam cover respectively, the groove of stepping down is seted up on the top surface of spraying case, the groove of stepping down sets up under the cam of keeping away from the locating plate, the U template sets up the below at another cam, the one end of U template runs through the support bar of locating bar after-fixing at the middle part.
Preferably, a second gear is fixedly sleeved on the outer side of one end, away from the supporting block, of the rotating shaft, a third rack is fixedly arranged on the top surface of the supporting table, and the third rack is matched with the second gear.
Preferably, one side of the second gear is provided with a power accumulation mechanism, the power accumulation mechanism is used for driving the second gear to rotate continuously after the second gear is separated from the third rack, the power accumulation mechanism comprises a positioning cover, the positioning cover is sleeved on the outer side of the second gear, the positioning cover is fixed on the outer wall of the positioning plate, a volute spiral spring is arranged between the positioning cover and the second gear together, one end of the volute spiral spring is fixed on the second gear, and the other end of the volute spiral spring is fixed on the inner wall of the positioning cover.
Preferably, the outer side of the second gear is sleeved with a friction ring, the friction ring is fixed on the side wall of the second gear, one side of the friction ring is in friction contact with a friction plate, the contact positions of the friction ring and the friction plate are both provided with friction surfaces, one end of the friction plate is fixed with a support, and the support is fixed on the side wall of the positioning plate.
A coating method of a coating device for surface treatment of aircraft parts, the coating method comprising the steps of:
step one, installation: before coating, adhering and fixing shielding pieces on three side surfaces of the turbine blade, inserting the positioning end of the turbine blade into the positioning groove, and extruding and positioning the turbine blade through bolts to fix the turbine blade on the supporting block;
step two, conveying: starting a first motor, wherein an output shaft of the first motor drives belt pulleys to rotate, under the transmission action of conveying belts, the two belt pulleys synchronously rotate, the two conveying belts drive corresponding positioning plates to move, the corresponding supporting blocks and the corresponding turbine blades are driven to move by the positioning plates, and when the turbine blades move to the upper part of a spraying box, the first motor is turned off to stop the turbine blades;
step three, coating a concave surface: the position of the nozzle is adjusted through the coating mechanism, so that the nozzle maintains a close spraying distance with the turbine blade when the nozzle sprays the curved surface of the turbine blade;
step four, coating the convex surface: after one side of the turbine blade is sprayed, the turbine blade is driven to rotate through the clamping turnover mechanism, so that the turbine blade is turned over, and in the process of rotating and turning over the turbine blade, the nozzle position is readjusted through the coating mechanism, and the same spraying distance is continuously maintained;
step five, conveying and discharging: and starting the first motor to drive the conveying belt to move, so that the turbine blade after spraying is driven to be far away from the spraying box.
Compared with the prior art, the invention has the following beneficial effects:
firstly, in the process of turning over the rotating turbine blade, the nozzle position is readjusted through the coating mechanism, so that the same spraying distance is continuously maintained after the turbine blade is turned over, and the problem that the bonding strength and the hardness of a coating are reduced due to different spraying distances is further solved.
Second, turbine blade is in the state of sunken face down when removing the top position to the spraying case, at this moment, extrudees two electric arc shower nozzles of both sides downwards through first spring for the electric arc shower nozzle at middle part highly is higher than the electric arc shower nozzle of both sides, and then at the spraying in-process, makes the position of each electric arc shower nozzle all keep close with the spraying distance of curved surface, and then is favorable to reducing because the spraying distance is different, the influence that causes the coating.
Thirdly, drive the turbine blade turn-over through starting centre gripping turn-over mechanism, at the in-process of turbine blade turn-over, through the support bar of pushing mechanism promotion middle part downwards, when the support bar at middle part moves downwards, the support bar through relative displacement mechanism regulation both sides rises to make shower nozzle and turbine blade's bellying adaptation again, make the position of each electric arc shower nozzle keep close again with the spraying distance of curved surface, and then be favorable to reducing because the spraying distance is different, the influence that causes the coating.
Drawings
FIG. 1 is a flow chart of a method of the present invention;
FIG. 2 is a schematic view of the overall structure of the present invention;
FIG. 3 is a schematic diagram of the structure at A in FIG. 1 according to the present invention;
FIG. 4 is a schematic overall (bottom view) structure of the present invention;
FIG. 5 is a schematic view of the structure of the positioning plate, the supporting block and the positioning cover of the present invention;
FIG. 6 is a cross-sectional rear view of the positioning plate, the supporting block and the positioning cover of the present invention;
FIG. 7 is a schematic structural view (another position) of the positioning plate, the supporting block and the positioning cover of the present invention after the cross-section;
FIG. 8 is a schematic view of the structure of the spray booth of the present invention;
FIG. 9 is a schematic view of the structure at B in FIG. 8 according to the present invention;
FIG. 10 is a schematic view of the rear cross-section of the spray box of the present invention;
FIG. 11 is a schematic view of the structure of FIG. 10 at C in accordance with the present invention;
FIG. 12 is a schematic view of a turbine blade configuration of the present invention.
In the figure: 1. a support table; 2. a belt pulley; 3. a conveyor belt; 4. a first motor; 5. positioning a plate; 6. a rotating shaft; 7. a supporting block; 8. positioning a groove; 9. a turbine blade; 10. a spraying box; 11. a vertical plate; 12. rotating the disc; 13. an electric push rod; 14. the driving disc is pushed; 15. a second motor; 16. a strip-shaped through hole; 17. a sliding plate; 18. mounting holes; 19. an arc spray head; 1901. a discharge pipe; 20. a first spring; 21. a drive plate; 22. a supporting strip; 23. a threading slot; 24. a positioning bar; 25. a reciprocating screw rod; 26. a limiting rod; 27. a third motor; 28. a first gear; 29. a first rack; 30. a second rack; 31. a yielding groove; 32. a cam; 33. a second gear; 34. a third rack; 35. a positioning cover; 36. a volute spiral spring; 37. a friction ring; 38. a friction plate; 39. a friction surface; 40. a support; 41. u-shaped plate.
Detailed Description
The following description is provided to disclose the invention so as to enable any person skilled in the art to practice the invention. The preferred embodiments in the following description are given by way of example only, and other obvious variations will occur to those skilled in the art.
As shown in fig. 2 to 12, the coating device for surface treatment of the aircraft parts comprises a supporting table 1, wherein four belt pulleys 2 are rotatably connected to the top surface of the supporting table 1, every two of the four belt pulleys 2 are coaxially fixed, a conveying belt 3 is jointly connected to the two belt pulleys 2 at the same height in a transmission manner, a first motor 4 is fixed to the inner top surface of the supporting table 1, and an output shaft of the first motor 4 penetrates through the top surface of the supporting table 1 and then is coaxially fixed to one of the belt pulleys 2; a plurality of positioning plates 5 are arranged between the two conveyer belts 3, the upper ends and the lower ends of the positioning plates 5 are respectively fixed on the corresponding conveyer belts 3, the middle parts of the positioning plates 5 are rotatably connected with rotating shafts 6, supporting blocks 7 are fixed at one ends of the rotating shafts 6, positioning grooves 8 are formed in the supporting blocks 7, and the positioning grooves 8 are matched with turbine blades 9; the top surface of the supporting table 1 is fixedly communicated with a spraying box 10, the top surface of the spraying box 10 is provided with a clamping and turning-over mechanism, and the clamping and turning-over mechanism is used for driving the turbine blades 9 to turn over; a coating mechanism is arranged in the spraying box 10, and when the turbine blade 9 is turned over, the coating mechanism can adjust the position of a nozzle for spraying a metal coating to be matched with the corresponding curved surface on the turbine blade 9; when the turbine blade 9 of the engine works, in order to enable the turbine blade 9 of the engine to have the levels of thermal shock resistance, high-temperature corrosion resistance, thermal alternation resistance and complex stress, a metal coating needs to be coated on the turbine blade 9, most of the existing coating methods adopt an electric arc spraying method, the metal coating is coated on the turbine blade 9, in the electric arc spraying process, the distance between a spraying opening and the spraying surface is different, the bonding strength and the hardness of the coating can be influenced, but because the outer wall of the turbine blade 9 is arc-surface-shaped, when the turbine blade 9 is simply sprayed by a single electric arc spraying gun, the distance between the spraying opening and the spraying surface is difficult to maintain the same, and the uneven spraying of the coating is caused, the implementation mode of the invention can solve the problems, and the specific operation mode is as follows, two arc-surface and three side surfaces of the turbine blade 9 need to be coated with the coating independently, before coating, adhering fixed shielding pieces on three sides of a turbine blade 9 to prevent metal coatings from adhering to the three sides of the turbine blade 9 in a spraying process, inserting the positioning end of the turbine blade 9 into a positioning groove 8 during installation, extruding and positioning the turbine blade 9 through a bolt to fix the turbine blade 9 on a supporting block 7, then starting and driving a first motor 4, driving a belt pulley 2 to rotate by an output shaft of the first motor 4, synchronously rotating the four belt pulleys 2 under the transmission action of a conveying belt 3, driving a corresponding positioning plate 5 to move through two conveying belts 3, driving the corresponding supporting block 7 and the turbine blade 9 to move through the positioning plate 5, and when the turbine blade 9 moves to the upper part of a spraying box 10, closing the first motor 4 to stop the turbine blade 9 to facilitate the metal coating operation of the turbine blade 9, the position of the nozzle is adjusted through the coating mechanism, so that the nozzle maintains a similar spraying distance with the turbine blade 9 when the nozzle sprays the curved surface of the turbine blade 9, and the problem that the bonding strength and hardness of the coating are reduced due to different spraying distances is solved; after the spraying to the one side of turbine blade 9 is accomplished, drive turbine blade 9 through centre gripping turn-over mechanism and rotate, supporting shoe 7, axis of rotation 6 rotates along with turbine blade 9, make turbine blade 9 can carry out the turn-over, be convenient for carry out the spraying to the another side of turbine blade 9 through coating mechanism, and because turbine blade 9 one side is sunken form, another personally submits protruding form, therefore, also need readjust the position of spout after the turn-over, this embodiment is at the turbine blade 9 and rotates the in-process of turn-over, through the readjustment spout position of coating mechanism, be favorable to after the turn-over, continue to maintain the same spraying distance, and then further reduce because the spraying distance is different, lead to the problem that the bonding strength and the hardness of coating reduce.
As a further embodiment of the invention, the clamping and turning-over mechanism comprises a vertical plate 11, the vertical plate 11 is fixed on the outer wall of the spraying box 10, one side of the vertical plate 11 is rotatably connected with a rotating disc 12, one side of the rotating disc 12 far away from the vertical plate 11 is fixed with an electric push rod 13, the tail end of a piston rod of the electric push rod 13 is fixed with a jacking disc 14, the other side of the vertical plate 11 is fixed with a second motor 15, and an output shaft of the second motor 15 penetrates through the vertical plate 11 and then is fixed with the rotating disc 12; in operation, only one end of the turbine blade 9 is positioned, and the turbine blade 9 is easy to shake during the arc spraying process, which causes uneven spraying, and the embodiment of the invention can solve the problems, and the specific operation mode is as follows, after the turbine blade 9 moves to the upper part of the spraying box 10, by starting the electric push rod 13, the piston rod top of the electric push rod 13 drives the ejector disk 14 to move to the side close to the turbine blade 9, the turbine blades 9 are positioned by extrusion, which in turn facilitates maintaining the stability of the turbine blades 9 during the spraying process, and by starting the second motor 15, the second motor 15 drives the rotating disc 12 to rotate, the rotating disc 12 drives the electric push rod 13, the rotating disc 12 and the turbine blades 9 to rotate, thereby, the turning operation of the turbine blade 9 can be performed, and the other side of the turbine blade 9 can be coated conveniently.
As a further embodiment of the invention, the coating mechanism comprises a strip-shaped through hole 16, the strip-shaped through hole 16 is arranged on the top surface of the spraying box 10, a sliding plate 17 is slidably connected inside the strip-shaped through hole 16, three mounting holes 18 are arranged on the sliding plate 17, arc nozzles 19 are arranged below the three mounting holes 18, the bottom of each arc nozzle 19 is connected with an external wire feeder, a control system, a power supply and a compressed air supply system through pipelines, a discharge pipe 1901 of each arc nozzle 19 penetrates through the corresponding mounting hole 18 and extends out, first springs 20 are jointly fixed between the arc nozzles 19 and the sliding plate 17 on two sides, the first springs 20 are sleeved outside the discharge pipe 1901, a driving plate 21 is fixed on the bottom surface of the sliding plate 17, a reciprocating driving mechanism is arranged on one side of the driving plate 21 and used for driving the driving plate 21 to reciprocate along the strip-shaped through hole 16, the bottom of each arc nozzle 19 is connected with a support bar 22 in a sliding manner, the support bar 22 in the middle is higher than the support bars 22 on the two sides, the top surfaces of the support bars 22 are provided with threading grooves 23, two ends of each of the three support bars 22 are provided with relative displacement mechanisms, a pushing mechanism is arranged above the support bar 22 in the middle, the pushing mechanism pushes the support bar 22 in the middle downwards in the rotating and turning-over process of the turbine blades 9, and when the support bar 22 in the middle moves downwards, the relative displacement mechanisms regulate the support bars 22 on the two sides to ascend; when the spraying device works, the turbine blade 9 is in a state that the concave surface faces downwards when moving to the position above the spraying box 10, at the moment, the two arc spray heads 19 on the two sides are downwards extruded through the first spring 20, so that the height of the arc spray head 19 in the middle is higher than that of the arc spray heads 19 on the two sides, further, in the spraying process, the position of each arc spray head 19 is kept close to the spraying distance of the curved surface, further, the influence on a coating due to different spraying distances is favorably reduced, in addition, the driving plate 21, the sliding plate 17 and the three arc spray heads 19 can be driven to move along the strip-shaped through hole 16 by starting the reciprocating moving mechanism, the arc spray heads 19 slide on the supporting strips 22, the moving spraying is convenient to be carried out below the turbine blade 9, in the moving process, the pipeline of each arc spray head 19 can slide in the threading groove 23, and the arc spray heads 19 respectively slide with the external wire feeder through the pipeline, Control system, power and compressed air feed system are connected, after one side spraying of turbine blade 9 is accomplished, through starting centre gripping turn-over mechanism and drive turbine blade 9 turn-over, at the in-process of turbine blade 9 turn-over, support bar 22 at the middle part is promoted downwards through pushing mechanism, when the support bar 22 of middle part moves down, it rises to adjust the support bar 22 that drives both sides through relative displacement mechanism, thereby make shower nozzle and turbine blade 9's protruding face adaptation again, make the position of each arc shower nozzle 19 keep close again with the spraying distance of curved surface, and then be favorable to reducing because the spraying distance is different, the influence that causes the coating.
As a further embodiment of the invention, the reciprocating driving mechanism comprises two positioning bars 24, the positioning bars 24 are respectively arranged at two ends of the bar-shaped through hole 16, the positioning bars 24 are both fixed on the inner top surface of the spraying box 10, a reciprocating screw rod 25 and a limiting rod 26 are jointly arranged between the two positioning bars 24, two ends of the reciprocating screw rod 25 are both rotatably connected on the positioning bars 24, two ends of the limiting rod 26 are both fixed on the positioning bars 24, the reciprocating screw rod 25 is in threaded connection with the driving plate 21, the limiting rod 26 is in sliding connection with the driving plate 21, a third motor 27 is fixed at one side of the positioning bars 24, and an output shaft of the third motor 27 penetrates through the positioning bars 24 and then is fixed with the reciprocating screw rod 25; during operation, by starting the third motor 27, the output shaft of the third motor 27 drives the reciprocating screw rod 25 to rotate, so that the driving plate 21 can move on the reciprocating screw rod 25, the other end of the driving plate 21 is guided and limited by the limiting rod 26, the driving plate 21 drives the sliding plate 17 and the three arc nozzles 19 to move, the reciprocating function is completed, and the three arc nozzles 19 can be conveniently moved and sprayed on the bottom surface of the turbine blade 9.
As a further embodiment of the present invention, the relative displacement mechanism includes two first gears 28, the two first gears 28 are respectively located between two adjacent support bars 22, two sides of each first gear 28 are provided with a first rack 29 and a second rack 30, the two second racks 30 are respectively fixed on the side walls of the support bars 22 at two sides, the two first racks 29 are fixed on the side walls of the support bars 22 at the middle part, the two first gears 28 are rotatably connected to the positioning bar 24, and the first gears 28 are simultaneously meshed with the adjacent first racks 29 and the adjacent second racks 30; in operation, when the pushing mechanism pushes the supporting bar 22 at the middle part downwards, the supporting bar 22 at the middle part moves downwards, thereby driving the two first racks 29 to move downwards, the two first racks 29 drive the first gear 28 to rotate, the two first gears 28 drive the two second racks 30 to move upwards, thereby driving the supporting bars 22 at the two sides to move upwards, so that the supporting bars 22 at the two sides are higher than the supporting bar 22 at the middle part, so that the arc spray heads 19 at the two sides are higher than the arc spray heads 19 at the middle part, which is beneficial for adapting the arc spray heads 19 and the convex surfaces of the turbine blades 9, when the later spraying is convenient, the spraying distances at the positions are kept close, thereby being beneficial for reducing the influence on the coating due to different spraying distances, when the supporting bar 22 at the middle part loses the pushing action of the pushing mechanism, under the pushing action of the first spring 20, the arc shower nozzle 19 of both sides drives the support bar 22 of both sides and moves down to make the support bar 22 in middle part drive the arc shower nozzle 19 rebound in middle part, resume initial position, this embodiment, through the altitude relation of automatically regulated middle part arc shower nozzle 19 and both sides arc shower nozzle 19, suit with turbine blade 9's curved surface, when making the spraying, the spraying distance of each position keeps close, is favorable to reducing because the spraying distance is different, the influence that causes the coating.
As a further embodiment of the present invention, the pushing mechanism includes a relief groove 31, a U-shaped plate 41, and two cams 32, the two cams 32 are respectively sleeved and fixed on the outer sides of the jacking disk 14 and the supporting block 7, the relief groove 31 is provided on the top surface of the spraying box 10, the relief groove 31 is provided right below the cam 32 far away from the positioning plate 5, the U-shaped plate 41 is provided below the other cam 32, and one end of the U-shaped plate 41 penetrates through the positioning strip 24 and then is fixed on the supporting strip 22 in the middle; in operation, when the concave surface of the turbine blade 9 is painted, the most distal end of the cam 32 is disposed at an end remote from the support bar 22, when the turbine blade 9 is turned over, the most distal end of the cam 32 is turned to the side near the support bar 22, one cam 32 penetrates through the abdicating groove 31, the supporting bar 22 at the middle part is pressed downwards by the two cams 32, the other cam 32 presses the U-shaped plate 41 downwards, so that the supporting bar 22 at the middle part moves downwards to complete the pushing function, by timely pushing the supporting bars 22 downwards, the height relationship between the middle arc nozzle 19 and the arc nozzles 19 at the two sides can be adjusted in time by linking the relative displacement mechanism after the turbine blade 9 turns over, the spraying distance of each position is kept close when the spraying is carried out by adapting to the curved surface of the turbine blade 9, which is beneficial to reducing the influence on the coating caused by different spraying distances.
As a further embodiment of the invention, a second gear 33 is sleeved and fixed on the outer side of one end of the rotating shaft 6 away from the supporting block 7, a third rack 34 is fixed on the top surface of the supporting table 1, and the third rack 34 is matched with the second gear 33; in operation, because the spraying surface of the turbine blade 9 is arc-shaped, after spraying is finished, the incompletely dried coating has a tendency to flow towards two sides of the turbine blade 9, which results in uneven coating on the dried turbine blade 9, the embodiment of the present invention can solve the above problems, specifically, in an operation mode that after spraying is finished, the conveyor belt 3 drives the positioning plate 5 to move again, the positioning plate 5 drives the corresponding supporting block 7, turbine blade 9 and second gear 33 to move, the second gear 33 moves towards one side close to the third rack 34, after the second gear 33 is meshed with the third rack 34, the second gear 33 rotates on the top surface of the third rack 34 in the moving process under the meshing action of the second gear 33 and the third rack 34, so that the rotating shaft 6 rotates, and the supporting block 7 and turbine blade 9 are driven to rotate by the rotating shaft 6, by slowly rotating the turbine blade 9, it is advantageous to uniformly distribute the metal coating on the turbine blade 9, and the metal coating on the turbine blade 9 is prevented from being deposited on both ends.
As a further embodiment of the present invention, a power storage mechanism is disposed on one side of the second gear 33, the power storage mechanism is configured to drive the second gear 33 to continue to rotate after the second gear 33 is disengaged from the third rack 34, the power storage mechanism includes a positioning cover 35, the positioning cover 35 is sleeved on the outer side of the second gear 33, the positioning cover 35 is fixed on the outer wall of the positioning plate 5, a spiral spring 36 is disposed between the positioning cover 35 and the second gear 33, one end of the spiral spring 36 is fixed on the second gear 33, and the other end of the spiral spring 36 is fixed on the inner wall of the positioning cover 35; in operation, because the conveyor belt 3 is provided with the plurality of turbine blades 9, when a new turbine blade 9 moves to the upper side of the spraying box 10, the conveyor belt 3 needs to be stopped, the new turbine blade 9 is sprayed, at this time, the turbine blade 9 after the previous spraying is stopped moving and then stops rotating, at this time, if the coating on the turbine blade 9 is not dried yet, the coating still has a tendency of flowing to both sides of the turbine blade 9, so that the coating on the dried turbine blade 9 is not uniform, the embodiment of the present invention can solve the above problem, specifically, the operation mode is as follows, when the second gear 33 rotates, the scroll spring 36 is driven to move, so that the scroll spring 36 generates torsion to store energy, and by setting the distance between the two positioning plates 5, after the first positioning plate 5 is separated from the third rack 34, the second positioning plate 5 just moves to the upper side of the spraying box 10, at this moment, the second gear 33 on the first positioning plate 5 is separated from the third rack 34, and at this moment, the volute spiral spring 36 drives the second gear 33 to rotate reversely under the action of torsion, so that when the turbine blade 9 on the second positioning plate 5 is sprayed, the turbine blade 9 on the first positioning plate 5 can still rotate automatically, and through slowly rotating the turbine blade 9, the metal coating on the turbine blade 9 is uniformly distributed, and the metal coating on the turbine blade 9 is prevented from being accumulated at two ends.
As a further embodiment of the present invention, a friction ring 37 is sleeved on the outer side of the second gear 33, the friction ring 37 is fixed on the side wall of the second gear 33, one side of the friction ring 37 is in friction contact with a friction plate 38, the contact positions of the friction ring 37 and the friction plate 38 are both provided with a friction surface 39, one end of the friction plate 38 is fixed with a bracket 40, and the bracket 40 is fixed on the side wall of the positioning plate 5; when the turbine blade slow-rotating device works, the friction ring 37 is in contact with the friction plate 38, when the volute spiral spring 36 drives the second gear 33 to rotate, the friction ring 37 is in frictional contact with the friction plate 38, so that the rotating speed of the second gear 33 is favorably reduced, the second gear 33 drives the turbine blade 9 to slowly rotate, and the rotating time is prolonged.
A coating method of a coating apparatus for surface treatment of an aircraft component as shown in fig. 1, the coating method comprising the steps of:
step one, installation: before coating, adhering and fixing shielding sheets on three side surfaces of the turbine blade 9, inserting the positioning end of the turbine blade 9 into the positioning groove 8, and extruding and positioning the turbine blade 9 through a bolt to fix the turbine blade 9 on the supporting block 7;
step two, conveying: starting the first motor 4, driving the belt pulleys 2 to rotate by an output shaft of the first motor 4, synchronously rotating the two belt pulleys 2 under the transmission action of the conveying belts 3, driving the corresponding positioning plates 5 to move through the two conveying belts 3, driving the corresponding supporting blocks 7 and the corresponding turbine blades 9 to move through the positioning plates 5, and turning off the first motor 4 when the turbine blades 9 move to the upper part of the spraying box 10 so as to stop the turbine blades 9 from moving;
step three, coating a concave surface: the position of the nozzle is adjusted through the coating mechanism, so that the nozzle can maintain a close spraying distance with the turbine blade 9 when the nozzle sprays the curved surface of the turbine blade 9;
step four, coating the convex surface: after the spraying of one side of the turbine blade 9 is finished, the turbine blade 9 is driven to rotate through the clamping and turning-over mechanism, so that the turbine blade 9 is turned over, and in the process of rotating and turning over the turbine blade 9, the nozzle position is readjusted through the coating mechanism, and the same spraying distance is continuously maintained;
step five, conveying and discharging: the first motor 4 is started to drive the conveyer belt 3 to move, so that the turbine blade 9 after spraying is driven to be far away from the spraying box 10.
The working principle of the invention is as follows:
two arc surfaces and three side surfaces of the turbine blade 9 need to be coated with coatings independently, before coating, three side surfaces of the turbine blade 9 need to be adhered with fixed shielding sheets, so that the three side surfaces of the turbine blade 9 are prevented from being adhered with metal coatings in the spraying process, when the spraying device is installed, the positioning end of the turbine blade 9 is inserted into the positioning groove 8, the turbine blade 9 is extruded and positioned through bolts, so that the turbine blade 9 is fixed on the supporting block 7, then the output shaft of the first motor 4 drives the belt pulley 2 to rotate by driving the first motor 4, under the transmission action of the conveying belts 3, the two belt pulleys 2 synchronously rotate, the corresponding positioning plate 5 is driven by the two conveying belts 3 to move, the corresponding supporting block 7 and the turbine blade 9 are driven by the positioning plate 5 to move, when the turbine blade 9 moves to the upper part of the spraying box 10, the first motor 4 is closed, the turbine blade 9 stops moving, the operation of coating the metal coating on the turbine blade 9 is facilitated, and the position of the nozzle is adjusted through the coating mechanism, so that the spraying distance close to the maintenance of the turbine blade 9 is kept when the nozzle sprays the curved surface of the turbine blade 9, and the problem that the bonding strength and hardness of the coating are reduced due to different spraying distances is solved; after the spraying to the one side of turbine blade 9 is accomplished, drive turbine blade 9 through centre gripping turn-over mechanism and rotate, supporting shoe 7, axis of rotation 6 rotates along with turbine blade 9, make turbine blade 9 can carry out the turn-over, be convenient for carry out the spraying to the another side of turbine blade 9 through coating mechanism, and because turbine blade 9 one side is sunken form, another personally submits protruding form, therefore, also need readjust the position of spout after the turn-over, this embodiment is at the turbine blade 9 and rotates the in-process of turn-over, through the readjustment spout position of coating mechanism, be favorable to after the turn-over, continue to maintain the same spraying distance, and then further reduce because the spraying distance is different, lead to the problem that the bonding strength and the hardness of coating reduce.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined by the appended claims and their equivalents.
Claims (10)
1. A coating device for surface treatment of aircraft parts, comprising a support table (1), characterized in that: the top surface of the supporting table (1) is rotatably connected with four belt pulleys (2), the four belt pulleys (2) are coaxially fixed in pairs, the two belt pulleys (2) at the same height are jointly connected with a conveying belt (3) in a transmission manner, a first motor (4) is fixed on the inner top surface of the supporting table (1), and an output shaft of the first motor (4) penetrates through the top surface of the supporting table (1) and is coaxially fixed with one of the belt pulleys (2);
a plurality of positioning plates (5) are arranged between the two conveying belts (3), the upper ends and the lower ends of the positioning plates (5) are respectively fixed on the corresponding conveying belts (3), the middle parts of the positioning plates (5) are rotatably connected with rotating shafts (6), one ends of the rotating shafts (6) are fixedly provided with supporting blocks (7), positioning grooves (8) are formed in the supporting blocks (7), and the positioning grooves (8) are matched with turbine blades (9);
a spraying box (10) is fixedly communicated with the top surface of the supporting table (1), a clamping and turning-over mechanism is arranged on the top surface of the spraying box (10), and the clamping and turning-over mechanism is used for driving the turbine blade (9) to turn over;
the spraying box (10) is internally provided with a coating mechanism, and when the turbine blade (9) turns over, the coating mechanism can adjust the position of a nozzle for spraying a metal coating to be matched with a corresponding curved surface on the turbine blade (9).
2. The coating device for surface treatment of aircraft parts according to claim 1, characterized in that: centre gripping turn-over mechanism includes riser (11), riser (11) are fixed on the outer wall of spraying case (10), one side rotation of riser (11) is connected with rolling disc (12), one side that riser (11) were kept away from in rolling disc (12) is fixed with electric putter (13), the piston rod end of electric putter (13) is fixed with a driving disk (14), the opposite side of riser (11) is fixed with second motor (15), the output shaft of second motor (15) runs through behind riser (11) and is fixed mutually with rolling disc (12).
3. The coating device for surface treatment of aircraft parts according to claim 1, wherein: the coating mechanism comprises a strip-shaped through hole (16), the strip-shaped through hole (16) is formed in the top surface of the spraying box (10), a sliding plate (17) is connected to the interior of the strip-shaped through hole (16) in a sliding mode, three mounting holes (18) are formed in the sliding plate (17), arc spray heads (19) are arranged below the three mounting holes (18), the bottoms of the arc spray heads (19) are connected with an external wire feeder, a control system, a power supply and a compressed air supply system through pipelines, discharge pipes (1901) of the arc spray heads (19) penetrate through the corresponding mounting holes (18) and extend out, first springs (20) are jointly fixed between the arc spray heads (19) on the two sides and the sliding plate (17), the first springs (20) are sleeved on the outer sides of the discharge pipes (1901), and a driving plate (21) is fixed on the bottom surface of the sliding plate (17), one side of drive plate (21) is provided with reciprocal actuating mechanism, reciprocal actuating mechanism is used for driving drive plate (21) along bar shape through-hole (16) reciprocating motion, every the equal sliding connection in bottom of arc shower nozzle (19) has support bar (22), the middle part support bar (22) highly be higher than the support bar (22) of both sides, threading groove (23), three have all been seted up on the top surface of support bar (22) the both ends of support bar (22) all are provided with relative displacement mechanism, the middle part support bar (22) top is provided with pushing mechanism, rotates the in-process of turn-over at turbine blade (9), pushing mechanism promotes support bar (22) at middle part downwards, when support bar (22) the downstream at middle part, relative displacement mechanism adjusts the support bar (22) of both sides and rises.
4. A coating apparatus for surface treatment of aircraft parts according to claim 3, wherein: reciprocal actuating mechanism includes two location strips (24), location strip (24) set up the both ends at bar through-hole (16) respectively, location strip (24) are all fixed on the interior top surface of spraying case (10), two be provided with reciprocal lead screw (25) and gag lever post (26) between location strip (24) jointly, the both ends of reciprocal lead screw (25) are all rotated and are connected on location strip (24), the both ends of gag lever post (26) are all fixed on location strip (24), reciprocal lead screw (25) and drive plate (21) threaded connection, gag lever post (26) and drive plate (21) sliding connection, one side of location strip (24) is fixed with third motor (27), the output shaft of third motor (27) runs through behind location strip (24) and reciprocal lead screw (25) is fixed mutually.
5. The coating device for surface treatment of aircraft parts according to claim 4, characterized in that: relative displacement mechanism includes two first gears (28), two first gear (28) are located respectively between two adjacent support bars (22), every the both sides of first gear (28) all are provided with first rack (29) and second rack (30), two second rack (30) are fixed respectively on support bar (22) lateral wall of both sides, two support bar (22) lateral wall at the middle part is all fixed in first rack (29), two first gear (28) are all rotated and are connected on location strip (24), first gear (28) mesh with adjacent first rack (29) and second rack (30) mutually simultaneously.
6. The coating device for surface treatment of aircraft parts according to claim 4, characterized in that: pushing mechanism establishes the outside of fixing at top driving disk (14) and supporting shoe (7) including groove (31), U template (41), two cam (32) cover respectively, groove (31) of stepping down sets up on the top surface of spraying case (10), groove (31) of stepping down sets up under cam (32) of keeping away from locating plate (5), U template (41) set up the below at another cam (32), the one end of U template (41) runs through location strip (24) after-fixing on support bar (22) at the middle part.
7. The coating device for surface treatment of aircraft parts according to claim 1, characterized in that: a second gear (33) is fixedly sleeved on the outer side of one end, far away from the supporting block (7), of the rotating shaft (6), a third rack (34) is fixed on the top surface of the supporting table (1), and the third rack (34) is matched with the second gear (33).
8. The coating device for surface treatment of aircraft parts according to claim 7, characterized in that: one side of second gear (33) is provided with and holds power mechanism, it is used for driving second gear (33) and continue to rotate after second gear (33) breaks away from third rack (34) to hold power mechanism, it includes location cover (35) to hold power mechanism, the outside at second gear (33) is established to location cover (35), location cover (35) are fixed on the outer wall of locating plate (5), be provided with volute spring (36) between location cover (35) and second gear (33) jointly, the one end of volute spring (36) is fixed on second gear (33), the other end of volute spring (36) is fixed on the inner wall of location cover (35).
9. The coating apparatus for surface treatment of aircraft parts according to claim 8, wherein: the outside cover of second gear (33) is equipped with friction ring (37), friction ring (37) are fixed on the lateral wall of second gear (33), one side friction contact of friction ring (37) has friction plate (38), the contact position of friction ring (37) and friction plate (38) all is provided with friction surface (39), the one end of friction plate (38) is fixed with support (40), support (40) are fixed on the lateral wall of locating plate (5).
10. A coating method of a coating device for surface treatment of an aircraft component, which is suitable for the coating device for surface treatment of an aircraft component according to any one of claims 1 to 9, characterized in that: the coating method comprises the following steps:
step one, installation: before coating, adhering and fixing shielding pieces on three side surfaces of the turbine blade (9), inserting the positioning end of the turbine blade (9) into the positioning groove (8), and extruding and positioning the turbine blade (9) through bolts to fix the turbine blade (9) on the supporting block (7);
step two, conveying: starting a first motor (4), driving a belt pulley (2) to rotate by an output shaft of the first motor (4), synchronously rotating two belt pulleys (2) under the transmission action of a conveying belt (3), driving a corresponding positioning plate (5) to move through the two conveying belts (3), driving a corresponding supporting block (7) and a corresponding turbine blade (9) to move through the positioning plate (5), and closing the first motor (4) when the turbine blade (9) moves to the upper part of a spraying box (10) so as to stop the turbine blade (9) from moving;
step three, coating a concave surface: the position of the nozzle is adjusted through the coating mechanism, so that the nozzle can maintain a close spraying distance with the turbine blade (9) when the nozzle sprays the curved surface of the turbine blade (9);
step four, coating the convex surface: after the spraying of one side of the turbine blade (9) is finished, the turbine blade (9) is driven to rotate through the clamping turnover mechanism, so that the turbine blade (9) is turned over, and in the process of rotating and turning over the turbine blade (9), the nozzle position is readjusted through the coating mechanism, and the same spraying distance is continuously maintained;
step five, conveying and discharging: and starting the first motor (4) to drive the conveying belt (3) to move, so that the turbine blade (9) after spraying is driven to be away from the spraying box (10).
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| CN115445825A (en) * | 2022-09-30 | 2022-12-09 | 安徽理工大学 | Turbine blade surface spraying upset subassembly |
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| CN214183671U (en) * | 2020-08-27 | 2021-09-14 | 刘瀛 | Aero-engine primary compressor blade spraying clamp |
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| US5065694A (en) * | 1990-08-20 | 1991-11-19 | Cooper Tire And Rubber Co. | Automatic white sidewall spraying apparatus |
| CN101884573A (en) * | 2010-05-27 | 2010-11-17 | 清华大学 | Multi-nozzle injection device for complex organ prosoma three-dimensional controlled forming machine |
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| CN114939485B (en) | 2022-10-18 |
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