CN115890179B - Self-adaptive fixing pin installation device for aero-engine - Google Patents
Self-adaptive fixing pin installation device for aero-engine Download PDFInfo
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- CN115890179B CN115890179B CN202211461070.8A CN202211461070A CN115890179B CN 115890179 B CN115890179 B CN 115890179B CN 202211461070 A CN202211461070 A CN 202211461070A CN 115890179 B CN115890179 B CN 115890179B
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- supporting
- supporting head
- aeroengine
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a self-adaptive fixing pin installation device of an aeroengine, which comprises a supporting pin and a supporting head, wherein a limiting fixing ring is sleeved outside the supporting pin, and at least three movable balls are embedded into one end of the limiting fixing ring, which faces the supporting head; at least three clamping grooves are formed in one end, facing the limiting fixed ring, of the supporting head, movable auxiliary pieces are clamped in each clamping groove, arc-shaped grooves are formed in one end, facing the limiting fixed ring, of each movable auxiliary piece, one end, facing the supporting head, of each movable ball is arranged in one arc-shaped groove in a matching mode, and when one end of each movable ball is arranged in the arc-shaped groove in a matching mode, a movable gap is formed between the supporting head and the limiting fixed ring; each movable ball is detachably connected with the supporting head through a connecting piece, and each movable ball penetrates through one movable auxiliary piece. The supporting pin and the supporting head can realize universal adjustment to a certain extent, so that size interference during installation is avoided, and the phenomenon of other strength of front and rear mounting points of the aeroengine is prevented.
Description
Technical Field
The invention belongs to the technical field of aero-engine installation, and particularly relates to a device for adaptively installing a fixing pin of an aero-engine.
Background
The aeroengine is a highly complex and precise thermodynamic machine, and is used as the heart of an airplane, not only the power of the airplane in flight, but also an important driving force for promoting the development of aviation industry, and each important change in the human aviation history is indistinguishable from the technical progress of the aeroengine. Brackets are often required to support and secure the engine during assembly, shipping and storage of the engine accessories.
At present, when an aeroengine and a bracket are assembled, two solid integrated fixing pins are generally used at the front part of the aeroengine, the mounting mode is easy to generate uneven stress and interference in size, and the processing requirement on the size of a fixing pin supporting piece is high. In addition, after the front part of the aero-engine is fixed, the phenomenon of extra strength is easy to occur when the rear supporting structure of the aero-engine is installed, so that the installation of the rear supporting structure is difficult, and the installation efficiency of the engine is low.
Aiming at the technology, the prior art with the authorized publication number of CN217452837U provides a solution, but the structure is complex, the practical realization of the structural flexibility is dependent on the clearance between the inner circumferential surface of the limit fixing ring and the outer circumferential surface of the supporting pin, but the clearance can lead the limit fixing ring and the supporting pin to generate collision friction, so that the limit fixing ring and the supporting pin can generate loss on a user and further influence the service life of the component, and therefore, a better technical scheme is needed to avoid the defects existing in the prior art.
Disclosure of Invention
The invention aims to provide an aeroengine self-adaptive fixing pin installation device which is used for solving the problems in the prior art.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the self-adaptive fixing pin installation device for the aero-engine comprises a supporting pin and a supporting head, wherein a limiting fixing ring is sleeved outside the supporting pin, and at least three movable balls are embedded into one end, facing the supporting head, of the limiting fixing ring; the support head is provided with at least three clamping grooves towards one end of the limiting fixed ring, movable auxiliary pieces are clamped in each clamping groove, arc-shaped grooves are formed in one end of each movable auxiliary piece towards the limiting fixed ring, each movable ball is arranged in one arc-shaped groove in a matched mode towards one end of the support head, and a movable gap is formed between the support head and the limiting fixed ring when one end of each movable ball is arranged in the arc-shaped groove in a matched mode; each movable ball is detachably connected with the supporting head through a connecting piece, and each movable ball penetrates through one movable auxiliary piece.
As a preferable technical scheme in the invention, the limiting fixing ring comprises two semicircular hoops, one surfaces of the two semicircular hoops facing the supporting pin are provided with U-shaped grooves, and the two semicircular hoops are connected and sleeved on the flange of the supporting pin through bolts.
As a preferable technical scheme in the invention, the other end of the movable auxiliary piece is provided with a rectangular limiting protrusion, the bottom of the clamping groove is provided with a rectangular limiting part, and the rectangular limiting protrusion is arranged in the rectangular limiting part in a matching way.
As a preferable technical scheme in the invention, the opening end of the clamping groove and the edge of the supporting head are arranged in a chamfering way.
As a preferable technical scheme in the invention, the connecting piece is a bolt, and a screw rod part of the bolt penetrates through the movable auxiliary piece and is in threaded connection with the corresponding movable ball.
As a preferred embodiment of the invention, the connecting element is screwed to the movable auxiliary element.
As a preferable technical scheme of the invention, a gasket is arranged between the nut end of the connecting piece and the supporting head.
As a preferable technical scheme in the invention, the connecting piece is a screw, one end of the screw is integrally formed with the movable ball or is in threaded connection with the movable ball, and the other end of the screw sequentially penetrates through the movable auxiliary piece and one end of the supporting head and is connected with the nut.
As a preferable technical scheme in the invention, a gasket is arranged between the nut and the supporting head.
As a preferable technical scheme in the invention, the bearing is connected to the outside of the supporting head, the inner ring of the bearing is fixedly connected with the supporting head, and the connecting piece is connected with the outer ring of the bearing.
The beneficial effects are that: the limiting fixed ring is sleeved outside the supporting pin, so that the supporting pin and the limiting fixed ring can rotate relatively, the flexibility and the self-adaptation capability of the self-adapting installation fixed pin device of the aeroengine are improved through the rotation relationship, the supporting head is contacted with the movable spherical surface of the supporting pin through the movable auxiliary piece, when the supporting head and the supporting pin need to be adjusted, the movable spherical surface can enable a certain angle between the supporting head and the supporting pin to change, the movable gap is a movable space with the angle change, a small range of movement is formed between the supporting head and the supporting pin, the dimensional interference of the aeroengine during installation is avoided, the phenomenon of strength difference of front and rear mounting points of the aeroengine is prevented, the machining difficulty of the size of a bracket of the aeroengine is reduced, and therefore the installation efficiency of the aeroengine is effectively improved; the movable auxiliary piece is clamped in the clamping groove of the supporting head, so that the movable auxiliary piece can be replaced according to actual conditions, stability and flexibility of the structure can be controlled under an optimal condition, when the movable auxiliary piece is assembled in the clamping groove, the stability of the movable auxiliary piece can be guaranteed, one end, facing the limiting fixing ring, of each movable auxiliary piece is provided with an arc-shaped groove, one end, facing the supporting head, of each movable ball is arranged in one arc-shaped groove in a matched mode, surface contact between the movable auxiliary piece and the movable ball is further kept, the structural stability during contact is further guaranteed, and damage to equipment caused by point contact is avoided; each movable ball is detachably connected with the supporting head through a connecting piece, and each movable ball penetrates through a movable auxiliary piece, so that the supporting pin and the supporting head are guaranteed to be stably connected while a certain movable range is reserved, and the supporting pin and the supporting head are guaranteed to be stable and adjustable.
Drawings
Fig. 1 is a schematic diagram of a connection structure according to the present invention.
In the figure: 1-a support pin; 101-flanges; 2-a support head; 3-limiting fixing rings; 4-a movable ball; 5-a mobile auxiliary; a 6-connector; 7-washers.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the present invention will be briefly described below with reference to the accompanying drawings and the description of the embodiments or the prior art, and it is obvious that the following description of the structure of the drawings is only some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort to a person skilled in the art. It should be noted that the description of these examples is for aiding in understanding the present invention, but is not intended to limit the present invention.
Embodiment one:
as shown in fig. 1, this embodiment provides an aero-engine self-adaptive installation fixing pin device, including a supporting pin 1 and a supporting head 2, a limiting fixing ring 3 is sleeved on the supporting pin 1, so that the supporting pin 1 and the limiting fixing ring 3 can rotate relatively, and further the flexibility and self-adaptation capability of the aero-engine self-adaptive installation fixing pin device are improved through the rotation relationship, at least three movable balls 4 are embedded into one end of the limiting fixing ring 3, which faces the supporting head 2, of the three movable balls 4 can rotate freely at one end of the limiting fixing ring 3, which faces the supporting head 2, and all the movable balls 4 are preferably arranged on the limiting fixing ring 3 in a uniformly distributed manner, so as to ensure the stability of the structure in the later connection use; the support head 2 is provided with at least three clamping grooves towards one end of the limit fixing ring 3, each clamping groove is internally provided with a movable auxiliary piece 5 in a clamping way, the movable auxiliary pieces 5 can be assembled and disassembled through the clamping grooves, the movable auxiliary pieces 5 can be replaced according to actual conditions, so that the stability and flexibility of the structure can be controlled under the best condition (as the structure of the two movable auxiliary pieces 5 in figure 1 is different, when the size difference is large enough, the stability and flexibility of the structure can be properly affected), when the movable auxiliary pieces 5 are assembled in the clamping grooves, the stability of the movable auxiliary pieces 5 can be ensured, one end of each movable auxiliary piece 5 towards the limit fixing ring 3 is provided with an arc-shaped groove, one end of each movable ball 4 towards the support head 2 is arranged in one arc-shaped groove in a matched way, further, the movable auxiliary piece 5 is kept in surface contact with the movable ball 4, so as to ensure the structural stability during contact, avoid damage to equipment caused by point contact, and when one end of the movable ball 4 is arranged in an arc-shaped groove in a matched manner, a movable gap is arranged between the support head 2 and the limiting fixed ring 3, the support head 2 is in surface contact with the movable ball 4 through the movable auxiliary piece 5, when the support head 2 and the support pin 1 need to be adjusted, the movable ball 4 can enable a certain angle between the support head 2 and the support pin 1 to change, the movable gap is a movable space with angle change, further, a small-range movement is formed between the support head 2 and the support pin 1, so that dimensional interference of an aeroengine is avoided during installation, the phenomenon of strength difference of front and rear mounting points of the aeroengine is prevented, the processing difficulty of the size of a bracket of the aeroengine is reduced, thereby effectively improving the installation efficiency of the aero-engine; each movable ball 4 is detachably connected with the supporting head 2 through a connecting piece 6, and each movable ball 4 penetrates through one movable auxiliary piece 5, so that the supporting pin 1 and the supporting head 2 are guaranteed to be stably connected while a certain movable range is reserved, and the supporting pin 1 and the supporting head 2 are guaranteed to be stable and adjustable.
According to the invention, the limiting fixed ring 3 is sleeved outside the supporting pin 1, so that the supporting pin 1 and the limiting fixed ring 3 can relatively rotate, the flexibility and the self-adaptation capability of the self-adaptation installation fixed pin device of the aeroengine are improved through the rotation relationship, the supporting head 2 is in surface contact with the movable ball 4 on the supporting pin 1 through the movable auxiliary piece 5, when the supporting head 2 and the supporting pin 1 need to be adjusted, the movable ball 4 can enable a certain angle change to be carried out between the supporting head 2 and the supporting pin 1, a movable gap is a movable space with the angle change, and further, a small range of movement is formed between the supporting head 2 and the supporting pin 1, so that the size interference is avoided when the aeroengine is installed, the phenomenon of strength difference of front and rear mounting points of the aeroengine is prevented, the processing difficulty of the size of a bracket of the aeroengine is reduced, and the installation efficiency of the aeroengine is effectively improved; the movable auxiliary piece 5 is clamped in the clamping groove of the supporting head 2, so that the movable auxiliary piece 5 can be replaced according to actual conditions, stability and flexibility of the structure can be controlled under an optimal condition, when the movable auxiliary piece 5 is assembled in the clamping groove, stability of the movable auxiliary piece 5 can be guaranteed, one end of each movable auxiliary piece 5, facing the limiting fixed ring 3, is provided with an arc-shaped groove, one end of each movable ball 4, facing the supporting head 2, is arranged in the arc-shaped groove in a matched mode, surface contact between the movable auxiliary piece 5 and the movable ball 4 is further kept, and structural stability during contact is guaranteed, so that damage to equipment caused by point contact is avoided; each movable ball 4 is detachably connected with the supporting head 2 through a connecting piece 6, and each movable ball 4 penetrates through one movable auxiliary piece 5, so that the supporting pin 1 and the supporting head 2 are guaranteed to be stably connected while a certain movable range is reserved, and the supporting pin 1 and the supporting head 2 are guaranteed to be stable and adjustable.
As a preferred embodiment in this embodiment, it should be further explained that the limiting fixing ring 3 includes two semicircular clips, one surface of the two semicircular clips facing the supporting pin 1 is provided with a U-shaped groove, and the two semicircular clips are connected by bolts and sleeved on the flange 101 of the supporting pin 1, so that the installation of the limiting fixing ring 3 can be realized on the basis of not damaging the structure of the supporting pin 1, and the limiting fixing ring 3 can also rotate on the flange 101 of the supporting pin 1, thereby improving the flexibility between the supporting head 2 and the supporting pin 1.
As a preferred implementation manner in this embodiment, it needs to be further explained that the other end of the movable auxiliary piece 5 is provided with a rectangular limiting protrusion, the bottom of the clamping groove is provided with a rectangular limiting portion, the rectangular limiting protrusion is arranged in the rectangular limiting portion in a matching manner, and the rectangular limiting protrusion is matched with the rectangular limiting portion, so that the movable auxiliary piece 5 is more stable after being mounted, and further the connection piece 6 is more easily and conveniently mounted.
As a preferred implementation manner in this embodiment, it needs to be further explained that, the opening end of the clamping groove and the edge of the supporting head 2 are both chamfered, the chamfer setting can avoid the occurrence of collision damage caused by contact at the angular position, so that the stability of the structure is better, and simultaneously, the supporting head 2 after chamfering is combined, when the supporting head 2 is adjusted relative to the supporting pin 1, if the supporting head 2 contacts with the supporting pin 1, the adjustment of the supporting head 2 is more natural, the collision at the angular position is avoided, and meanwhile, the chamfer at the angular position can avoid more adjustment space, so as to improve the flexibility.
As a preferred embodiment in this embodiment, it should be further described that the connecting piece 6 is a bolt, and the screw portion of the bolt passes through the movable auxiliary piece 5 and is in threaded connection with the corresponding movable ball 4, so that the connection mode is convenient, and the structural stability is good.
As a preferred embodiment of the present embodiment, it should be further explained that the connecting piece 6 is screwed with the movable auxiliary piece 5, so that the stability of the movable auxiliary piece 5 can be further enhanced, and at the same time, the threaded connection between the connecting piece 6 and the movable auxiliary piece 5 is convenient because the movable auxiliary piece 5 is clamped on the supporting head 2.
As a preferred embodiment in this example, it should be further explained that the washer 7 is disposed between the nut end of the connecting piece 6 and the supporting head 2, so as to reduce wear and ensure the service life of the apparatus.
Embodiment two:
the present embodiment is a further improvement made on the basis of the first embodiment, and the specific differences between the present embodiment and the first embodiment are:
as a preferred embodiment of the present invention, it should be further described that the connecting member 6 is a screw, one end of the screw is integrally formed with the movable ball 4 or is in threaded connection with the movable ball, and the other end of the screw sequentially passes through the movable auxiliary member 5 and one end of the supporting head 2 and is connected with a nut, so that the connection of the connecting member 6 is more convenient and stable.
As a preferred embodiment in this example, it should be further explained that a washer is provided between the nut and the support head 2, so that wear can be reduced, and the service life of the apparatus can be ensured.
Embodiment III:
the present embodiment is a further improvement made on the basis of the first embodiment or the second embodiment, and the specific differences between the present embodiment and the first embodiment or the second embodiment are:
as a preferred embodiment of the present invention, it should be further explained that the bearing is connected to the outside of the supporting head 2, the inner ring of the bearing is fixedly connected to the supporting head 2, and the connecting piece 6 is connected to the outer ring of the bearing, so as to avoid the rotation between the limiting fixing ring 3 and the supporting pin 1, further reduce the loss between the limiting fixing ring 3 and the supporting pin 1, and ensure the service life of the device.
Finally, it should be noted that: the foregoing description is only of the preferred embodiments of the invention and is not intended to limit the scope of the invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. The self-adaptive fixing pin installation device for the aero-engine comprises a supporting pin (1) and a supporting head (2), and is characterized in that a limiting fixing ring (3) is sleeved outside the supporting pin (1), and at least three movable balls (4) are embedded into one end, facing the supporting head (2), of the limiting fixing ring (3); the support head (2) is provided with at least three clamping grooves towards one end of the limiting fixed ring (3), movable auxiliary pieces (5) are clamped in each clamping groove, the matched movable auxiliary pieces (5) can be replaced according to actual conditions, arc-shaped grooves are formed in one end of each movable auxiliary piece (5) towards the limiting fixed ring (3), one end of each movable ball (4) towards the support head (2) is arranged in one arc-shaped groove in a matched mode, and when one end of each movable ball (4) is arranged in the arc-shaped groove in a matched mode, a movable gap is formed between the support head (2) and the limiting fixed ring (3); each movable ball (4) is detachably connected with the supporting head (2) through a connecting piece (6), and each movable ball (4) penetrates through one movable auxiliary piece (5); the other end of the movable auxiliary piece (5) is provided with a rectangular limiting protrusion, the bottom of the clamping groove is provided with a rectangular limiting part, and the rectangular limiting protrusion is arranged in the rectangular limiting part in a matching manner.
2. The device for adaptively installing the fixing pin of the aeroengine according to claim 1, wherein the limiting fixing ring (3) comprises two semicircular hoops, one surface of each semicircular hoop, which faces the supporting pin (1), is provided with a U-shaped groove, and the two semicircular hoops are connected and sleeved on the flange (101) of the supporting pin (1) through bolts.
3. An aeroengine self-adapting mounting fixing pin device according to claim 1, characterized in that the open end of the clamping groove and the edge of the supporting head (2) are both arranged in a chamfer.
4. An aeroengine self-adapting mounting fixing pin device according to claim 1, characterized in that the connecting piece (6) is a bolt, the shank of which passes through the movable auxiliary piece (5) and is screwed with the corresponding movable ball (4).
5. An aeroengine self-adapting mounting fixing pin device according to claim 4, wherein the connecting piece (6) is screwed with the mobile auxiliary piece (5).
6. An aeroengine self-adapting mounting fixing pin device according to claim 4, characterized in that a washer (7) is arranged between the nut end of the connecting piece (6) and the supporting head (2).
7. The device for adaptively installing a fixing pin of an aeroengine according to claim 1, wherein the connecting piece (6) is a screw, one end of the screw is integrally formed with or in threaded connection with the movable ball (4), and the other end of the screw sequentially passes through one end of the movable auxiliary piece (5) and one end of the supporting head (2) and is connected with a nut.
8. An aeroengine self-adapting mounting fixing pin device according to claim 7, characterized in that a washer is arranged between the nut and the supporting head (2).
9. An aeroengine self-adapting mounting fixing pin device according to any of claims 1-8, wherein the bearing is connected to the outside of the supporting head (2), the inner ring of the bearing is fixedly connected to the supporting head (2), and the connecting piece (6) is connected to the outer ring of the bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211461070.8A CN115890179B (en) | 2022-11-21 | 2022-11-21 | Self-adaptive fixing pin installation device for aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211461070.8A CN115890179B (en) | 2022-11-21 | 2022-11-21 | Self-adaptive fixing pin installation device for aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115890179A CN115890179A (en) | 2023-04-04 |
| CN115890179B true CN115890179B (en) | 2023-09-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211461070.8A Active CN115890179B (en) | 2022-11-21 | 2022-11-21 | Self-adaptive fixing pin installation device for aero-engine |
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| CN (1) | CN115890179B (en) |
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| Publication number | Publication date |
|---|---|
| CN115890179A (en) | 2023-04-04 |
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