CN111321405A - Electric spark multipoint parallel deposition mechanism for flame-retardant coating of aircraft engine case - Google Patents
Electric spark multipoint parallel deposition mechanism for flame-retardant coating of aircraft engine case Download PDFInfo
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- CN111321405A CN111321405A CN201811537334.7A CN201811537334A CN111321405A CN 111321405 A CN111321405 A CN 111321405A CN 201811537334 A CN201811537334 A CN 201811537334A CN 111321405 A CN111321405 A CN 111321405A
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- 230000008021 deposition Effects 0.000 title claims abstract description 95
- 238000010892 electric spark Methods 0.000 title claims abstract description 49
- 239000011248 coating agent Substances 0.000 title claims abstract description 47
- 238000000576 coating method Methods 0.000 title claims abstract description 47
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 title claims abstract description 40
- 239000003063 flame retardant Substances 0.000 title claims abstract description 40
- 230000007246 mechanism Effects 0.000 title claims abstract description 32
- 230000001681 protective effect Effects 0.000 claims abstract description 33
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 239000004677 Nylon Substances 0.000 claims description 2
- 238000002347 injection Methods 0.000 claims description 2
- 239000007924 injection Substances 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims description 2
- 229910001095 light aluminium alloy Inorganic materials 0.000 claims description 2
- 229920001778 nylon Polymers 0.000 claims description 2
- -1 polytetrafluoroethylene Polymers 0.000 claims description 2
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 2
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 2
- 238000011084 recovery Methods 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 abstract description 7
- 238000005137 deposition process Methods 0.000 abstract description 6
- 238000005728 strengthening Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 30
- 230000007547 defect Effects 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C26/00—Coating not provided for in groups C23C2/00 - C23C24/00
- C23C26/02—Coating not provided for in groups C23C2/00 - C23C24/00 applying molten material to the substrate
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Abstract
An electric spark multipoint parallel deposition mechanism for an aircraft engine case flame-retardant coating relates to a mechanism, in particular to an electric spark multipoint parallel deposition mechanism for an aircraft engine case flame-retardant coating. The invention aims to solve the problems that manual electric spark deposition efficiency of an aero-engine case flame-retardant coating is low and deposition quality is difficult to accurately control. The mechanism is based on a modular design and comprises a support supporting shaft, a support web plate, a support, a cam rotating device, a ball guide sleeve, an electrode rotary vibration device and a direction-adjustable protective gas pipeline. The numerical control technology and the electric spark deposition surface strengthening technology are combined to build an electric spark deposition process platform for the flame-retardant coating of the aero-engine case, so that the electric spark multi-point parallel deposition of the flame-retardant coating of the aero-engine case is realized. The invention can obtain the electric spark multi-point parallel deposition mechanism for the flame-retardant coating of the aircraft engine case.
Description
Technical Field
The invention relates to a special deposition mechanism, in particular to an electric spark multi-point parallel deposition mechanism for an aircraft engine case flame-retardant coating.
Background
The electric spark deposition technology has been widely applied to the fields of aviation, aerospace, military industry, tools, molds and the like due to the unique advantages (such as metallurgical bonding of the coating and the substrate, low energy input, small influence on thermal deformation and structural change of the substrate, fine and dense structure and good consistency of the deposited coating, small pollution to the environment, energy conservation and the like). However, the electric spark deposition process of the flame-retardant coating of the aircraft engine case still adopts a manual operation mode, and the manual operation can cause the problems of low deposition efficiency, unstable coating preparation quality, difficult control of coating appearance characteristics and the like.
Under the background of rapid development of a numerical control machine tool and a numerical control technology, the numerical control technology and an electric spark deposition surface strengthening technology are combined to build an electric spark deposition process platform of the flame-retardant coating of the aero-engine case, the numerical control precision control of the electric spark deposition process of the flame-retardant coating of the aero-engine case is realized by means of software and hardware development achievements of the numerical control technology, the defect of manual deposition is overcome, and therefore the precision control of the structure, the performance and the apparent characteristic of the coating is realized.
Disclosure of Invention
The invention aims to solve the problems that the electric spark deposition efficiency of the flame-retardant coating of the aero-engine case is low and the deposition quality is difficult to control, so that the electric spark multi-point parallel deposition mechanism of the flame-retardant coating of the aero-engine case is provided.
An electric spark multipoint parallel deposition mechanism for an aircraft engine case flame-retardant coating mainly comprises a support shaft, a support web plate, a support, a cam rotating device, a ball guide sleeve, an electrode rotary vibration device and a direction-adjustable protective gas pipeline; the bracket supporting shaft comprises a bracket supporting shaft body and a threaded hole for connecting the web plate; the bracket web comprises a bracket web body, a threaded hole for connecting a bracket supporting shaft and a threaded hole for connecting a bracket; the support comprises a support body, a cam rotating device mounting seat, a ball guide sleeve mounting hole, a fixed tension spring lower hook fixing seat threaded hole, a fixed direction-adjustable protective gas pipeline fixing piece threaded hole and a fixed support web plate threaded hole; the cam rotating device comprises a motor, a cam and a key; the ball guide sleeve comprises a sleeve and balls; the electrode rotary vibration device comprises an electrode, a set screw, an electrode holder, a deposition power supply positive terminal, a deposition power supply positive bearing, an electrode holder pin shaft, a spring, an insulating sleeve, a key, a screw, a tension spring upper fixing plate, a tension spring, a motor, a bolt, a nut, a roller fastener, a bearing, a roller pin shaft and a bearing retainer ring; the direction-adjustable protective gas pipeline comprises a protective gas hose joint, a protective gas pipeline and a direction-adjustable spherical nozzle;
the support back shaft is connected with the support web through bolts, the support web is connected with the support through bolts, a cam rotating device mounting seat and a ball guide sleeve mounting hole are arranged on the support, the cam rotating device is mounted in the cam rotating device mounting seat on the support, the ball guide sleeve is mounted in the ball guide sleeve mounting hole on the support, the electrode rotary vibration device is mounted in the ball guide sleeve, a hook under a tension spring is fixed on a lower fixing seat of the tension spring through a cylindrical pin, the lower fixing seat of the tension spring is fixed on the support through bolts, and the direction-adjustable protective gas pipeline fixing part for the direction-adjustable protective gas pipeline is fixed on the support through bolts.
Principles and advantages of the present invention.
The invention fully plays the function of a numerical control lathe, fixes an aircraft engine case on a three-jaw chuck of the numerical control lathe, clamps an aircraft engine case flame-retardant coating electric spark multi-point parallel deposition mechanism on a numerical control lathe tool rest through a support shaft, drives the aircraft engine case to do rotary motion through controlling the rotating speed of a main shaft of the numerical control lathe, drives the aircraft engine case flame-retardant coating electric spark parallel multi-point deposition mechanism to do feed motion through controlling the feed speed of the numerical control lathe, and realizes the aircraft engine case flame-retardant coating electric spark multi-point parallel deposition under the rotary vibration of an electrode of the aircraft engine case flame-retardant coating electric spark multi-point parallel deposition mechanism.
The invention realizes numerical control and automation of the electric spark deposition process of the flame-retardant coating of the aircraft engine case, overcomes the defects of manual deposition, and achieves accurate control of the structure, performance and apparent characteristics of the coating.
In order to solve the insulation problem of the power supply of the machine tool and the electric spark deposition machine, the invention designs the insulating sleeve for electric cutting on the electrode rotary vibration device, thereby ensuring the safety of the machine tool operator.
In order to solve the problem that the high-frequency pulse of the electric spark deposition machine is smoothly conducted to the electrode, the positive electrode bearing of the deposition power supply is arranged at the mounting part of the positive electrode bearing of the deposition power supply, and the positive electrode bearing of the deposition power supply has the following functions: firstly, the outer ring is still when the inner ring of the positive bearing of the deposition power supply rotates along with the electrode holder, so that the positive binding post of the deposition power supply is conveniently connected with the positive electrode of the power supply of the electric spark deposition machine; and secondly, the power supply positive electrode connected to the positive binding post of the deposition power supply can be transmitted to the electrode holder through the outer ring, the roller and the inner ring of the positive bearing of the deposition power supply and then transmitted to the electrode, so that the potential of the electrode is the same as that of the positive binding post of the deposition power supply.
And fifthly, the invention can obtain the electric spark multi-point parallel deposition mechanism for the flame-retardant coating of the aircraft engine case.
Drawings
Fig. 1 is a schematic structural diagram of a bracket supporting shaft according to a first embodiment.
Fig. 2 is a schematic structural diagram of a bracket web according to the first embodiment.
Fig. 3 is a schematic structural diagram of a stent according to a first embodiment.
Fig. 4 is a schematic structural diagram of a cam rotating device according to a first embodiment.
Fig. 5 is a schematic structural view of a ball guide sleeve according to a first embodiment.
Fig. 6 is a schematic structural diagram of an electrode rotational vibration apparatus according to a first embodiment.
Fig. 7 is a schematic structural diagram of a direction-adjustable shielding gas pipeline according to a first embodiment.
Fig. 8 is a schematic structural diagram of a direction-adjustable shielding gas pipe fixing member according to a first embodiment.
Fig. 9 is a schematic structural view of a lower tension spring fixing seat according to a first embodiment.
Fig. 10 is a schematic structural diagram of a cam according to the first embodiment.
Fig. 11 is a schematic structural diagram of an electrode according to the first embodiment.
Fig. 12 is a schematic structural diagram of an electrode holder according to the first embodiment.
Fig. 13 is a schematic structural diagram of a positive terminal of a deposition power supply according to the first embodiment.
Fig. 14 is a schematic structural diagram of a positive bearing of a deposition power supply according to the first embodiment.
Fig. 15 is a schematic structural diagram of a spring according to the first embodiment.
Fig. 16 is a schematic structural diagram of an insulating sleeve according to the first embodiment.
Fig. 17 is a schematic structural diagram of a key according to the first embodiment.
Fig. 18 is a schematic structural view of a fixing plate on a tension spring according to a first embodiment.
Fig. 19 is a schematic structural view of a tension spring according to the first embodiment.
Fig. 20 is a schematic structural view of a roller fastener according to the first embodiment.
Fig. 21 is a schematic structural view of a roller pin according to a first embodiment.
Fig. 22 is a schematic structural diagram of a retainer ring according to the first embodiment.
FIG. 23 is a schematic structural view of a ball nozzle with adjustable direction according to a first embodiment.
Fig. 24 is a schematic structural diagram of an electric spark multi-point parallel deposition mechanism for an aircraft engine case flame-retardant coating according to a first embodiment.
Detailed Description
The first embodiment is as follows: the embodiment is a multipoint parallel deposition mechanism for flame-retardant coating electric sparks of an aeroengine case, which comprises a support shaft (1), a support web (2), a support (3), a cam rotating device (4), a ball guide sleeve (5), an electrode rotary vibration device (6) and a direction-adjustable protective gas pipeline (7); the support supporting shaft (1) comprises a support supporting shaft body (1-1) and a threaded hole (1-2) for connecting the web plate; the support web (2) comprises a support web body (2-1), a threaded hole (2-2) for connecting a support shaft of the support and a threaded hole (2-3) for connecting the support; the support (3) comprises a support body (3-1), a cam rotating device mounting seat (3-2), a ball guide sleeve mounting hole (3-3), a fixed tension spring lower hook fixing seat threaded hole (3-4), a fixed direction-adjustable protective gas pipeline fixing piece threaded hole (3-5) and a fixed support web plate threaded hole (3-6); the cam rotating device (4) comprises a motor (4-1), a cam (4-2) and a key (4-3); the ball guide sleeve (5) comprises a sleeve (5-1) and balls (5-2); the electrode rotary vibration device (6) comprises an electrode (6-1), a set screw (6-2), an electrode holder (6-3), a deposition power supply positive terminal (6-4), a deposition power supply positive bearing (6-5), an electrode holder pin shaft (6-6), a spring (6-7), an insulating sleeve (6-8), a key (6-9), a screw (6-10), a tension spring upper fixing plate (6-11), a tension spring (6-12), a motor (6-13), a bolt (6-14), a nut (6-15), a roller fastener (6-16), a roller (6-17), a roller pin shaft (6-18) and a bearing retainer ring (6-19); the direction-adjustable protective gas pipeline (7) comprises a protective gas hose joint (7-1), a protective gas pipeline (7-2) and a direction-adjustable spherical nozzle (7-3);
the support supporting shaft (1) is connected with a support web plate (2) through a bolt (10), the support web plate (2) is connected with a support (3) through a bolt (11), the support (3) is provided with a cam rotating device mounting seat (3-2) and a ball guide sleeve mounting hole (3-3), a cam rotating device (4) is mounted in the cam rotating device mounting seat (3-2) on the support (3), a ball guide sleeve (5) is mounted in the ball guide sleeve mounting hole (3-3) on the support (3), an electrode rotary vibration device (6) is mounted in the ball guide sleeve (5), a tension spring lower hook (19-3) is fixed on a tension spring lower fixing seat (9) through a cylindrical pin (12), the tension spring lower fixing seat (9) is fixed on the support (3) through bolt connection, the direction-adjustable protective gas pipeline (7) is fixed on the bracket (3) through bolt connection by using a direction-adjustable protective gas pipeline fixing piece (8).
Fig. 1 is a schematic structural diagram of a bracket supporting shaft according to a first embodiment: in FIG. 1, (1-1) is a bracket supporting shaft body, and (1-2) is a threaded hole for connecting a web plate;
fig. 2 is a schematic structural diagram of a bracket web according to a first embodiment: in FIG. 2, (2-1) is a bracket web body, (2-2) is a threaded hole for connecting a bracket supporting shaft, and (2-3) is a threaded hole for connecting a bracket;
fig. 3 is a schematic structural diagram of a stent according to a first embodiment: in FIG. 3, (3-1) is a bracket body, (3-2) is a cam rotating device mounting seat, (3-3) is a ball guide sleeve mounting hole, (3-4) is a fixed tension spring lower hook fixing seat threaded hole, (3-5) is a fixed direction-adjustable protective gas pipeline fixing part threaded hole, and (3-6) is a fixed bracket web plate threaded hole;
fig. 4 is a schematic structural diagram of a cam rotating device according to a first embodiment: in FIG. 4, (4-1) is a motor, (4-2) is a cam, and (4-3) is a key;
fig. 5 is a schematic structural view of a ball guide sleeve according to a first embodiment: in FIG. 5, (5-1) is a sleeve and (5-2) is a ball;
fig. 6 is a schematic structural diagram of an electrode rotational vibration apparatus according to a first embodiment: in fig. 6, (6-1) is an electrode, (6-2) is a set screw, (6-3) an electrode holder, (6-4) is a deposition power supply anode binding post, (6-5) is a deposition power supply anode bearing, (6-6) is an electrode holder pin shaft, (6-7) is a spring, (6-8) is an insulating sleeve, (6-9) is a key, (6-10) is a screw, (6-11) is a tension spring upper fixing plate, (6-12) is a tension spring, (6-13) is a motor, (6-14) is a bolt, (6-15) is a nut, (6-16) is a roller fastener, (6-17) is a roller, (6-18) is a roller pin shaft, and (6-19) is a bearing retainer ring;
fig. 7 is a schematic structural diagram of a direction-adjustable shielding gas pipeline according to a first embodiment: in FIG. 7, (7-1) is a protective gas hose connector, (7-2) is a protective gas pipeline, and (7-3) is an adjustable direction ball-type nozzle;
fig. 8 is a schematic structural diagram of a direction-adjustable shielding gas pipe fixing member according to a first embodiment: in FIG. 8, (8-1) is a bolt connecting hole, and (8-2) is an adjustable direction protection gas pipeline fixing part;
fig. 9 is a schematic structural view of a lower tension spring fixing seat according to a first embodiment: in FIG. 9, (9-1) is a cylindrical pin connecting hole, and (9-2) is a bolt connecting hole;
FIG. 10 is a schematic view of a cam according to one embodiment;
FIG. 11 is a schematic structural diagram of an electrode according to one embodiment;
fig. 12 is a schematic structural diagram of an electrode holder according to a first embodiment: in FIG. 12, (12-1) is a fastening screw connection hole, (12-2) is an electrode clamping portion, (12-3) is a deposition power supply anode bearing mounting portion, and (12-4) is an electrode holder pin shaft mounting hole;
FIG. 13 is a schematic structural view of a positive terminal of a deposition power supply according to one embodiment;
FIG. 14 is a schematic structural diagram of a positive bearing of a deposition power supply according to one embodiment;
FIG. 15 is a schematic diagram of a spring according to one embodiment;
fig. 16 is a schematic structural diagram of an insulating sleeve according to a first embodiment: in FIG. 16, (16-1) is a pin shaft slideway of the electrode holder, (16-2) is a key groove, and (16-3) is a motor rotating shaft mounting part;
FIG. 17 is a schematic view of a key according to one embodiment;
fig. 18 is a schematic structural view of a fixing plate on a tension spring according to a first embodiment: in FIG. 18, (18-1) is a screw connection hole, and (18-2) is a hook fixing part on the tension spring;
fig. 19 is a schematic structural view of a tension spring according to a first embodiment: in FIG. 19, (19-1) is an upper hook of a tension spring, (19-2) is a body of the tension spring, and (19-3) is a lower hook of the tension spring;
fig. 20 is a schematic structural view of a roller fastener according to the first embodiment: in FIG. 20, (20-1) is a bolt connecting hole, and (20-2) is a roller pin connecting hole;
fig. 21 is a schematic structural view of a roller pin according to a first embodiment;
FIG. 22 is a schematic view of a retainer ring according to one embodiment;
FIG. 23 is a schematic structural view of a ball-type adjustable nozzle according to one embodiment;
fig. 24 is a schematic structural diagram of an electric spark multi-point parallel deposition mechanism for an aircraft engine case flame retardant coating according to a first embodiment: in the figure, (1) is a support shaft, (2) is a support web, (3) is a support, (4) is a cam rotating device, (5) is a ball guide sleeve, (6) is an electrode rotating and vibrating device, (7) is a direction-adjustable protective gas pipeline, (8) is a protective gas pipeline fixing part, (9) is a tension spring lower fixing seat, (10) is a bolt for connecting the support shaft (1) and the support web (2), (11) is a bolt for connecting the support web (2) and the support (3), and (12) is a cylindrical pin.
Principles and advantages of this embodiment.
The method fully plays the function of a numerical control lathe, fixes an aircraft engine case on a three-jaw chuck of the numerical control lathe, clamps the flame-retardant coating electric spark multi-point parallel deposition mechanism of the aircraft engine case on a tool rest of the numerical control lathe through a support supporting shaft (1), drives the aircraft engine case to rotate through controlling the rotating speed of a main shaft of the numerical control lathe, drives the flame-retardant coating electric spark multi-point parallel deposition mechanism of the aircraft engine case to feed through controlling the feeding speed of the numerical control lathe, and realizes the flame-retardant coating electric spark multi-point parallel deposition of the aircraft engine case under the rotary vibration of an electrode (6-1) of the flame-retardant coating electric spark multi-point parallel deposition mechanism of the aircraft engine case.
The implementation mode realizes numerical control and automation of the electric spark deposition process of the flame-retardant coating of the aircraft engine case, overcomes a plurality of defects of manual deposition, and achieves accurate control of the structure, performance and apparent characteristics of the coating.
In order to solve the problem of insulation between the machine tool and the power supply of the electric spark deposition machine, the electrode rotary vibration device (6) is provided with an insulating sleeve (6-8) for electric cutting, so that the safety of a machine tool operator is ensured.
Fourthly, in order to solve the problem that the high-frequency pulse of the electric spark deposition machine is smoothly conducted to the electrode (6-1), the positive bearing (6-5) of the deposition power supply is arranged at the positive bearing mounting part (12-3) of the deposition power supply, and the function of the positive bearing (6-5) of the deposition power supply is as follows: firstly, the outer ring is still when the inner ring of the positive bearing (6-5) of the deposition power supply rotates along with the electrode holder (6-3), so that the positive wiring terminal (6-4) of the deposition power supply is conveniently connected with the positive electrode of the power supply of the electric spark deposition machine; and secondly, the power supply positive electrode connected to the deposition power supply positive terminal (6-4) can be transmitted to the electrode holder (6-3) through the outer ring, the roller and the inner ring of the deposition power supply positive bearing (6-5) and then transmitted to the electrode (6-1), so that the potential of the electrode (6-1) is the same as that of the deposition power supply positive terminal (6-4).
Fifth, this embodiment can obtain a flame retardant coating electric spark multi-point parallel deposition mechanism of aeroengine machine casket.
The second embodiment is as follows: the present embodiment differs from the first embodiment in that: the outer contour of the support supporting shaft (1) is a regular hexagon, the inner contour is a square, and the support supporting shaft is made of steel with better rigidity. The rest is the same as the first embodiment.
The third concrete implementation mode: the present embodiment is different from the first or second embodiment in that: the support web plate (2) is L-shaped and made of steel with better rigidity. The others are the same as in the first or second embodiment.
The fourth concrete implementation mode: the present embodiment differs from the first to third embodiments in that: the support (3) is in a regular dodecagon shape and is made of light aluminum alloy. The others are the same as the first to third embodiments.
The fifth concrete implementation mode: the present embodiment differs from the first to fourth embodiments in that: the electrode (6-1) is a rod-shaped electrode and is fixed on the electrode clamping part (12-2) through a set screw (6-2), the rotating speed of the electrode (6-1) is controlled through the rotating speed of a motor (6-13), and the up-and-down vibration of the electrode (6-1) is realized through the rotation of a cam (4-2) and the stretching deformation and the recovery of a tension spring (6-12). The rest is the same as the first to fourth embodiments.
The sixth specific implementation mode: the present embodiment differs from the first to fifth embodiments in that: the deposition power supply positive terminal (6-4) is used for being connected with a deposition power supply positive electrode, the aircraft engine case is connected with a deposition power supply negative electrode, the deposition power supply positive terminal (6-4) is welded on an outer ring of a deposition power supply positive bearing (6-5), the deposition power supply positive bearing (6-5) is installed on a deposition power supply positive bearing installation part (12-3), and the deposition power supply positive bearing (6-5) is an industrial bearing. The rest is the same as the first to fifth embodiments.
The seventh embodiment: the present embodiment differs from the first to sixth embodiments in that: the insulating sleeve (6-8) is made of nylon or polytetrafluoroethylene, the insulating sleeve (6-8) is connected with the motor (6-13) through a key (6-9), a spring (6-7) is arranged in the insulating sleeve (6-8), the electrode (6-1) is driven by the electrode holder (6-3), the springs (6-7) can be compressed in the insulating sleeves (6-8) to avoid the rigid collision between the electrode (6-1) and the aeroengine casing, the electrode holder (6-3) is fixed in the insulating sleeve (6-8) through an electrode holder pin shaft (6-6), and the electrode holder pin shaft (6-6) can slide up and down in the insulating sleeve electrode holder pin shaft slideway (16-1) under the drive of the electrode holder (6-3). The rest is the same as the first to sixth embodiments.
The specific implementation mode is eight: the present embodiment differs from the first to seventh embodiments in that: the upper fixing plate (6-11) of the tension spring is fixed on the motor (6-13) through a screw (6-10). The rest is the same as the first to seventh embodiments.
The specific implementation method nine: the present embodiment differs from the first to eighth embodiments in that: the roller (6-17) is fixed on the roller fastener (6-16) through a roller pin shaft (6-18) and a bearing retainer ring (6-19), the roller fastener (6-16) is fixed on the rear part of the motor (6-13) through a bolt (6-14) and a nut (6-15), and the roller (6-17) is an industrial bearing. The others are the same as the first to eighth embodiments.
The detailed implementation mode is ten: the present embodiment differs from the first to ninth embodiments in that: the motors (6-13) can rapidly respond to the vertical vibration of the ball guide sleeve (5) through rolling friction. The rest is the same as the first to ninth embodiments.
The concrete implementation mode eleven: the present embodiment differs from the first to tenth embodiments in that: the direction-adjustable protective gas pipeline (7) is characterized in that the gas injection direction can be adjusted by rotating the direction-adjustable spherical nozzle (7-3), and the direction-adjustable protective gas pipeline (7) is fixed on the support (3) through bolt connection by using a direction-adjustable protective gas pipeline fixing piece (8). The rest is the same as the first to tenth embodiments.
Claims (10)
1. The utility model provides an aeroengine machine casket flame retardant coating electric spark multi-point parallel deposition mechanism which characterized in that: the device consists of a support supporting shaft (1), a support web plate (2), a support (3), a cam rotating device (4), a ball guide sleeve (5), an electrode rotary vibration device (6) and a direction-adjustable protective gas pipeline (7); the support supporting shaft (1) comprises a support supporting shaft body (1-1) and a threaded hole (1-2) for connecting the web plate; the support web (2) comprises a support web body (2-1), a threaded hole (2-2) for connecting a support shaft of the support and a threaded hole (2-3) for connecting the support; the support (3) comprises a support body (3-1), a cam rotating device mounting seat (3-2), a ball guide sleeve mounting hole (3-3), a fixed tension spring lower hook fixing seat threaded hole (3-4), a fixed direction-adjustable protective gas pipeline fixing piece threaded hole (3-5) and a fixed support web plate threaded hole (3-6); the cam rotating device (4) comprises a motor (4-1), a cam (4-2) and a key (4-3); the ball guide sleeve (5) comprises a sleeve (5-1) and balls (5-2); the electrode rotary vibration device (6) comprises an electrode (6-1), a set screw (6-2), an electrode holder (6-3), a deposition power supply positive terminal (6-4), a deposition power supply positive bearing (6-5), an electrode holder pin shaft (6-6), a spring (6-7), an insulating sleeve (6-8), a key (6-9), a screw (6-10), a tension spring upper fixing plate (6-11), a tension spring (6-12), a motor (6-13), a bolt (6-14), a nut (6-15), a roller fastener (6-16), a roller (6-17), a roller pin shaft (6-18) and a bearing retainer ring (6-19); the direction-adjustable protective gas pipeline (7) comprises a protective gas hose joint (7-1), a protective gas pipeline (7-2) and a direction-adjustable spherical nozzle (7-3); the support supporting shaft (1) is connected with a support web plate (2) through a bolt (10), the support web plate (2) is connected with a support (3) through a bolt (11), the support (3) is provided with a cam rotating device mounting seat (3-2) and a ball guide sleeve mounting hole (3-3), a cam rotating device (4) is mounted in the cam rotating device mounting seat (3-2) on the support (3), a ball guide sleeve (5) is mounted in the ball guide sleeve mounting hole (3-3) on the support (3), an electrode rotary vibration device (6) is mounted in the ball guide sleeve (5), a tension spring lower hook (19-3) is fixed on a tension spring lower fixing seat (9) through a cylindrical pin (12), the tension spring lower fixing seat (9) is fixed on the support (3) through bolt connection, the direction-adjustable protective gas pipeline (7) is fixed on the bracket (3) through bolt connection by using a direction-adjustable protective gas pipeline fixing piece (8).
2. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the outer contour of the support supporting shaft (1) is a regular hexagon, the inner contour is a square, and the support supporting shaft is made of steel with better rigidity.
3. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the support web plate (2) is L-shaped and made of steel with better rigidity.
4. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the support (3) is in a regular dodecagon shape and is made of light aluminum alloy.
5. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the electrode (6-1) is a rod-shaped electrode and is fixed on the electrode clamping part (12-2) through a set screw (6-2), the rotating speed of the electrode (6-1) is controlled through the rotating speed of a motor (6-13), and the up-and-down vibration of the electrode (6-1) is realized through the rotation of a cam (4-2) and the stretching deformation and the recovery of a tension spring (6-12).
6. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the deposition power supply positive terminal (6-4) is used for being connected with a deposition power supply positive electrode, the aircraft engine case is connected with a deposition power supply negative electrode, the deposition power supply positive terminal (6-4) is welded on an outer ring of a deposition power supply positive bearing (6-5), the deposition power supply positive bearing (6-5) is installed on a deposition power supply positive bearing installation part (12-3), and the deposition power supply positive bearing (6-5) is an industrial bearing.
7. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the insulating sleeve (6-8) is made of nylon or polytetrafluoroethylene, the insulating sleeve (6-8) is connected with the motor (6-13) through a key (6-9), a spring (6-7) is arranged in the insulating sleeve (6-8), the electrode (6-1) is driven by the electrode holder (6-3), the springs (6-7) can be compressed in the insulating sleeves (6-8) to avoid the rigid collision between the electrode (6-1) and the aeroengine casing, the electrode holder (6-3) is fixed in the insulating sleeve (6-8) through an electrode holder pin shaft (6-6), and the electrode holder pin shaft (6-6) can slide up and down in the insulating sleeve electrode holder pin shaft slideway (16-1) under the drive of the electrode holder (6-3).
8. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the upper fixing plate (6-11) of the tension spring is fixed on the motor (6-13) through a screw (6-10).
9. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the roller (6-17) is fixed on the roller fastener (6-16) through a roller pin shaft (6-18) and a bearing retainer ring (6-19), the roller fastener (6-16) is fixed on the rear part of the motor (6-13) through a bolt (6-14) and a nut (6-15), and the roller (6-17) is an industrial bearing.
10. The aircraft engine case flame retardant coating electric spark multi-point parallel deposition mechanism as claimed in claim 1, wherein: the direction-adjustable protective gas pipeline (7) is characterized in that the gas injection direction can be adjusted by rotating the direction-adjustable spherical nozzle (7-3), and the direction-adjustable protective gas pipeline (7) is fixed on the support (3) through bolt connection by using a direction-adjustable protective gas pipeline fixing piece (8).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811537334.7A CN111321405A (en) | 2018-12-15 | 2018-12-15 | Electric spark multipoint parallel deposition mechanism for flame-retardant coating of aircraft engine case |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811537334.7A CN111321405A (en) | 2018-12-15 | 2018-12-15 | Electric spark multipoint parallel deposition mechanism for flame-retardant coating of aircraft engine case |
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