CN220097200U - Quick-release device for aero-engine mounting joint - Google Patents
Quick-release device for aero-engine mounting joint Download PDFInfo
- Publication number
- CN220097200U CN220097200U CN202321348761.7U CN202321348761U CN220097200U CN 220097200 U CN220097200 U CN 220097200U CN 202321348761 U CN202321348761 U CN 202321348761U CN 220097200 U CN220097200 U CN 220097200U
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- upper shaft
- shaft cover
- gasket
- seat
- groove
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- 238000009434 installation Methods 0.000 claims abstract description 11
- 230000009467 reduction Effects 0.000 claims description 9
- 238000007789 sealing Methods 0.000 claims description 3
- 238000004806 packaging method and process Methods 0.000 abstract description 6
- 238000013016 damping Methods 0.000 abstract description 5
- 238000012856 packing Methods 0.000 abstract description 5
- 230000007246 mechanism Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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- Vibration Prevention Devices (AREA)
Abstract
The utility model relates to the field of aeroengine packaging, and particularly discloses an aeroengine mounting joint quick-release device which comprises a shaft seat, an upper shaft cover, a through groove, a limit rod and a fastening piece, wherein the shaft seat is arranged on a support frame, the upper shaft cover is hinged with the shaft seat, the through groove vertically penetrates through the side wall of the shaft seat and the side wall of the upper shaft cover and is outwards opened, the limit rod can rotate into the through groove and is contacted with the inner wall of the through groove, and the fastening piece can fix the upper end of the limit rod on the top surface of the upper shaft cover. The problem that current aeroengine installation festival and installing support's connection structure in the packing box did not have quick dismantlement and damping function can be solved to this scheme.
Description
Technical Field
The utility model relates to the field of aero-engine packaging, in particular to a quick-release device for an aero-engine mounting joint.
Background
The installation joint mechanism bears the main load of the aeroengine, is an important component for transmitting the thrust of the aeroengine to the aircraft, and is also a main positioning mechanism of the aeroengine on the aircraft. In the flight process of the aircraft, various loads are transmitted to the engine through the mounting joint mechanism, in short, the mounting joint mechanism utilizes the pin shaft to simultaneously penetrate through the side wall of the aircraft engine and the mounting hole on the aircraft to position the engine, so that the engine is also positioned by utilizing the point of the mounting joint in transportation.
At present, an aeroengine is mainly supported by adopting 4 supporting points of a main mounting joint and an auxiliary mounting joint in the transportation process, the aeroengine is connected with a supporting frame on a packaging box through the 4 supporting points, as described in Chinese patent publication No. CN114955231A, the utility model discloses a clamp assembly for connecting the aeroengine and the supporting frame on the packaging box, the clamp assembly comprises a first clamp with a concave part, a second clamp and a fastener, mounting holes are formed in the concave parts of the two clamps relatively, and the fastener adopts at least 4 screws with more than M16 and is used for detachably and threadedly connecting the first clamp with the second clamp.
The defects are that: 1. when the aircraft engine is transported to a destination, the complete machine assembly is required, and when the existing supporting points are disassembled, at least more than 15 seconds are required for disassembling a single screw (the time for converting the disassembling process is not counted), at least 1 minute is required for disassembling at least 16 screws for 4 supporting points, and at least 4 minutes is required for disassembling at least 16 screws for 4 supporting points. The 4 minutes appear to be very short, but are critical to the maintainability and safeguarding of the munitions. 2. Because aircraft engine is the complex precise structure that numerous parts constitute, require the engine to alleviate the influence of jolting to the engine in the transportation as far as possible in the transportation, and the outside bush of round pin axle in above-mentioned scheme is direct with clamp inner wall circumference contact, both hard striking when jolting, four supporting points in the packing transport case all receive the vibration.
Disclosure of Invention
The utility model provides a quick-release device for an aeroengine mounting joint, which aims to solve the problem that the connecting structure of the existing aeroengine mounting joint and a mounting bracket in a packaging box does not have the functions of quick disassembly and vibration reduction.
In order to solve the problems, the utility model adopts the following technical scheme: the quick-release device for the aeroengine mounting joint comprises a shaft seat, an upper shaft cover and a fastener for fixing the shaft seat and the upper shaft cover, wherein the upper shaft cover is hinged on the shaft seat, a semicircular groove capable of accommodating a pin shaft is formed in the opposite surface of the upper shaft cover and the shaft seat, and an elastic piece is connected between the semicircular groove and the pin shaft in a sealing manner; the utility model discloses a seat body, including upper shaft cover, pivot seat, fastener, threaded section, removable gasket, threaded connection, removable nut, the upper shaft cover top surface's logical groove outer edge is opened there is the antiskid of joint gasket to put down the platform, upper shaft cover and the one end that the pivot seat kept away from the pin joint is opened there is vertical logical groove, the fastener includes that one end articulates the gag lever post of seat body logical groove lateral wall, and the free end of gag lever post is equipped with the screw thread section, and the screw thread section overcoat has detachable gasket and threaded connection has detachable nut.
The principle of the scheme is as follows: when the aeroengine is fixed, the elastic piece is installed on the outer wall of the pin shaft of the installation joint structure, then the elastic piece is horizontally placed into the semicircular groove of the shaft seat, the upper shaft cover is rotated and closed, the outer wall of the pin shaft is tightly pressed between the upper shaft cover and the shaft seat, meanwhile, the limiting rod is rotated to enable the limiting rod to be completely contacted in the through groove, the gasket penetrates through the limiting rod and is clamped into the anti-slip sinking table, so that the limiting rod is prevented from rotating, the nut is sleeved on the limiting rod and screwed tightly, the gasket is pressed between the nut and the anti-slip sinking table, and the installation joint pin shaft is fixed.
The beneficial effect of this scheme is:
1. the connecting mode of aeroengine and packing box supporting point is the clamp of disconnect-type from top to bottom among the prior art, need use four at least screws to connect as an organic wholely with both when fixed upper and lower clamp, dismantle with the time that the installation screw used more on four supporting points, this scheme adopts articulated last shaft cap and axle bed, the lock only needs to rotate single gag lever post and screw up single nut and can install after the round pin axle outer wall is preliminary location to the round pin axle, need not repeatedly to align last shaft cap and axle bed, during the dismantlement, only need unscrew nut, ejecting gasket can quick separation go up shaft cap and axle bed, the action flow is smooth and fast.
2. The existing installation festival round pin axle is the rigid contact with between the clamp subassembly, and vibration in the transportation can cause round pin axle outer wall and clamp inner wall friction of colliding with, this scheme is at the outer wall sealing connection elastic component of round pin axle, utilizes the deformation of elastic component to fill the installation space, and the installation is firm, and the influence to the supporting point that jolts is reduced as far as possible through elastic contraction simultaneously, alleviates the vibration.
Further, the elastic piece comprises a plurality of rubber vibration reduction rings sleeved along the length of the pin shaft, a detachable bushing is sleeved between the rubber vibration reduction rings and the pin shaft, the bushing is a cylinder formed by two spliced semicircular sheets, annular ribs extend out of two ends of the bushing along the circumferential direction, and the distance between the annular ribs at the two ends is equal to the width of the upper shaft cover. The convex edges on the bushings are contacted with the end surfaces of the upper shaft cover and the lower shaft cover to position the mounting points of the pin shafts, and meanwhile, the mounting range of the rubber vibration reduction ring is limited, so that the rubber vibration reduction ring is prevented from slipping and shifting.
Further, the fastener is a T-shaped rotary screw, the horizontal section of the rotary screw is rotationally connected to one side of the shaft seat, which is close to the free end of the upper shaft cover, and the vertical section of the rotary screw is sleeved with a gasket and a nut.
Further, the through groove and the anti-slip sinking table are coaxially arranged.
Further, the lower end of the shaft seat is provided with a plurality of vertical mounting holes. The device is convenient to fix with the packing box, and the quick-release device can be installed in a matching way according to the size and strength requirements of the engine.
Further, the gasket is annular, the inner wall of the anti-slip sinking table is an arc surface attached to the gasket. And (5) the stress condition on the side wall of the gasket is uniform.
Drawings
FIG. 1 is an overall schematic of an embodiment of the present utility model;
FIG. 2 is a schematic view of a partial explosion of an embodiment of the present utility model;
FIG. 3 is an overall exploded view of an embodiment of the present utility model.
Detailed Description
The following is a further detailed description of the embodiments:
reference numerals in the drawings of the specification include: axle bed 1, first articulated ear 101, upper shaft cover 2, semicircle groove 21, second articulated ear 102, connecting pin 3, rotatory screw rod 4, nut 5, gasket 6, anti-skidding platform 7, bush 8, bead 81, rubber damping ring 9, round pin axle 10, logical groove 12.
The axial direction of the pin shaft 10 is in the x direction, the horizontal radial direction of the pin shaft 10 is in the y direction, and the vertical radial direction of the pin shaft 10 is in the z direction, and the direction is taken as a reference.
An embodiment is substantially as shown in fig. 1 to 3:
the lower end of the shaft seat 1 is in a horizontal rectangular plate shape, the upper end of the shaft seat 1 is a rectangular block with a semicircular groove on the top surface, a first hinge lug 101 along the x direction is integrally formed on the top wall of one end of the rectangular block in the y direction, a bridge-type upper shaft cover 2 is buckled above the rectangular block, the semicircular groove 21 formed by upwards sinking is formed on the bottom surface of the upper shaft cover 2, the upper shaft cover 2 is opposite to the two semicircular grooves 21 on the rectangular block, a round hole through which a pin shaft 10 of a mounting joint structure can penetrate is spliced, a second hinge lug 102 is integrally formed at one end of the upper shaft cover 2, close to the first hinge lug 101, of the second hinge lug 102 is contacted with two ends of the first hinge lug 101, and a connecting pin 3 is penetrated in the first hinge lug 101 and the second hinge lug 102 at the same time, so that the upper shaft cover 2 can be hinged with the rectangular block of the shaft seat 1. The top surface of the first hinge lug 101 is an arc surface protruding upwards, the side wall, close to the first hinge lug 101, of the upper shaft cover 2 is an arc surface recessed along the y direction, so that the upper shaft cover 2 is prevented from being blocked by the hinge lug when the upper shaft cover 2 rotates to a vertical state along the connecting pin 3, and the upper shaft cover 2 can be horizontally opened to 180 degrees.
The vertical through groove 12 recessed along the y direction is machined at one end of the upper shaft cover 2 and the shaft seat 1 moment block far away from the connecting pin 3, the bottom surface of the through groove 12 is an arc surface, one end of the shaft seat 1 moment block close to the through groove 12 is rotationally connected with the T-shaped rotary screw 4, one section of the rotary screw 4 hinged with the shaft seat 1 is a horizontal section, the rotary screw 4 is vertical to the horizontal section, the vertical section can rotate to the inside of the vertical through groove 12 and contacts with the inner wall of the vertical through groove 12, and a nut 5 is connected to the vertical section in a threaded manner.
The vertical through groove 12 penetrates through the top surface of the upper shaft cover 2 to machine an anti-slip sinking table 7, the anti-slip sinking table 7 is an annular groove recessed along the z direction, the annular groove and the arc surface of the vertical through groove 12 are coaxially arranged, but the edge of the annular groove expands outwards towards the circumference of the through groove 12 to form a step capable of accommodating the circular gasket 6. When the rotary screw 4 rotates to be contacted with the inner wall of the through groove 12, the circular gasket 6 is sleeved on the rotary screw, the circular gasket 6 is clamped in the anti-slip sinking table 7 to limit the rotation of the rotary screw 4, and then the nut 5 is screwed to tightly press the circular gasket 6 in the anti-slip sinking table 7.
The bushing 8 is movably sleeved on the outer wall of the pin shaft 10 penetrating between the upper shaft cover 2 and the shaft seat 1, the bushing 8 is composed of two semicircular covers, the two semicircular covers are spliced into a cylinder shape after being attached to the outer wall of the pin shaft 10, the two ends of the bushing 8 are respectively provided with a convex rib 81 extending along the circumferential direction, the distance between the convex ribs 81 at the two ends is the same as the x-direction length of the upper shaft cover 2, and a plurality of rubber damping rings 9 are sleeved on the outer wall of the bushing 8 between the two convex ribs 81, so that the rubber damping rings 9 can be attached to the inner walls of the upper shaft cover 2 and the shaft seat 1 when the pin shaft 10 is installed in the installation joint quick-release device of the embodiment, and the installation gap is filled and plays a role of elastic damping.
The specific implementation process is as follows:
when the engine is fixed in the packaging box, the bushing 8 is buckled on the outer wall of the pin shaft 10 of the mounting joint structure, the rubber vibration reduction ring 9 is sleeved and fully distributed on the outer wall of the bushing 8, one end of the bushing 8 is placed in the semicircular groove 21 of the shaft seat 1, the upper shaft cover 2 is turned over to enable the inner wall of the upper shaft cover 2 to be in contact with the outer wall of the bushing 8, the rotary screw 4 is completely rotated into the through groove 12, the circular gasket 6 passes through the upper end of the rotary screw 4 and is integrally clamped into the anti-slip sinking table 7, the nut 5 passes through the upper end of the rotary screw 4 and is screwed, and the circular gasket 6 is tightly pressed between the anti-slip sinking table 7 and the nut 5;
when the engine is quickly disassembled from the packing box supporting frame, the nuts 5 are unscrewed, the circular gaskets 6 are taken down, the rotary screw 4 integrally rotates out of the through grooves 12, the upper shaft cover 2 is opened to release the fixation of the pin shafts 10, the rubber vibration reduction rings 9 are taken down one by one, and finally the bushings 8 are disassembled.
The foregoing is merely exemplary embodiments of the present utility model, and specific structures and features that are well known in the art are not described in detail herein. It should be noted that modifications and improvements can be made by those skilled in the art without departing from the structure of the present utility model, and these should also be considered as the scope of the present utility model, which does not affect the effect of the implementation of the present utility model and the utility of the patent. The protection scope of the present utility model is subject to the content of the claims, and the description of the specific embodiments and the like in the specification can be used for explaining the content of the claims.
Claims (6)
1. The utility model provides an aeroengine installation festival quick detach device, includes axle bed, upper shaft cover, the fastener of fixing axle bed and upper shaft cover, its characterized in that: the upper shaft cover is hinged on the shaft seat, a semicircular groove capable of accommodating the pin shaft is formed in the opposite surface of the upper shaft cover and the shaft seat, and an elastic piece is connected between the semicircular groove and the pin shaft in a sealing manner; the utility model discloses a seat body, including upper shaft cover, pivot seat, fastener, threaded section, removable gasket, threaded connection, removable nut, the upper shaft cover top surface's logical groove outer edge is opened there is the antiskid of joint gasket to put down the platform, upper shaft cover and the one end that the pivot seat kept away from the pin joint is opened there is vertical logical groove, the fastener includes that one end articulates the gag lever post of seat body logical groove lateral wall, and the free end of gag lever post is equipped with the screw thread section, and the screw thread section overcoat has detachable gasket and threaded connection has detachable nut.
2. The quick release device for an aircraft engine mounting joint according to claim 1, wherein: the elastic piece comprises a plurality of rubber vibration reduction rings sleeved along the length of the pin shaft, a detachable bushing is sleeved between the rubber vibration reduction rings and the pin shaft, the bushing is a cylinder formed by two spliced semicircular sheets, annular ribs extend out of two ends of the bushing along the circumferential direction, and the distance between the annular ribs at the two ends is equal to the width of the upper shaft cover.
3. The quick release device for an aircraft engine mounting joint according to claim 1, wherein: the fastener is a T-shaped rotary screw rod, the horizontal section of the rotary screw rod is rotationally connected to one side of the shaft seat, which is close to the free end of the upper shaft cover, and the vertical section of the rotary screw rod is sleeved with a gasket and a nut.
4. The quick release device for an aircraft engine mounting joint according to claim 1, wherein: the through groove and the anti-slip sinking table are coaxially arranged.
5. The quick release device for an aircraft engine mounting joint according to claim 1, wherein: the lower end of the shaft seat is provided with a plurality of vertical mounting holes.
6. The quick release device for an aircraft engine mounting joint according to claim 1, wherein: the gasket is annular, the inner wall of the anti-slip sinking table is an arc surface attached to the gasket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321348761.7U CN220097200U (en) | 2023-05-30 | 2023-05-30 | Quick-release device for aero-engine mounting joint |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321348761.7U CN220097200U (en) | 2023-05-30 | 2023-05-30 | Quick-release device for aero-engine mounting joint |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220097200U true CN220097200U (en) | 2023-11-28 |
Family
ID=88865326
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321348761.7U Active CN220097200U (en) | 2023-05-30 | 2023-05-30 | Quick-release device for aero-engine mounting joint |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220097200U (en) |
-
2023
- 2023-05-30 CN CN202321348761.7U patent/CN220097200U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant |