CN115890179A - Self-adaptive mounting fixing pin device for aero-engine - Google Patents
Self-adaptive mounting fixing pin device for aero-engine Download PDFInfo
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- CN115890179A CN115890179A CN202211461070.8A CN202211461070A CN115890179A CN 115890179 A CN115890179 A CN 115890179A CN 202211461070 A CN202211461070 A CN 202211461070A CN 115890179 A CN115890179 A CN 115890179A
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- 238000009434 installation Methods 0.000 claims abstract description 23
- 230000000694 effects Effects 0.000 claims abstract description 12
- 230000003044 adaptive effect Effects 0.000 claims 7
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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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 fixed pin mounting device for an aircraft engine, 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 in one end of the limiting fixing ring, which faces the supporting head; the supporting head is provided with at least three clamping grooves towards one end of the limiting fixing ring, a movable auxiliary part is clamped in each clamping groove, an arc-shaped groove is formed in one end of each movable auxiliary part towards the limiting fixing ring, one end of each movable ball towards the supporting head is arranged in one arc-shaped groove in a matched mode, and when one end of each movable ball is arranged in the arc-shaped groove in a matched mode, a movable gap is formed between the supporting head and the limiting fixing ring; every activity ball all can dismantle with supporting the head through the connecting piece and be connected, and every activity ball all passes a activity auxiliary member. The support pin and the support head can realize universal adjustment to a certain degree, avoid size interference during installation and prevent the phenomenon of stiffness of front and rear installation points of an aircraft engine.
Description
Technical Field
The invention belongs to the technical field of aeroengine installation, and particularly relates to a self-adaptive fixing pin installation device for an aeroengine.
Background
The aircraft engine is a highly complex and precise thermal machine, is used as the heart of an aircraft, is not only the power of the aircraft flight, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine. Brackets are often used to support and secure the engine during assembly, shipping and storage of the engine accessories.
At present, when an aero-engine is assembled with a bracket, two solid and integrated fixing pins are generally used in the front of the aero-engine, the mounting mode is prone to uneven stress and size interference, and the requirement for machining the size of a fixing pin supporting piece is high. In addition, after the front part of the aircraft engine is fixed, a phenomenon of stiffness is easy to occur when the rear supporting structure of the aircraft engine is installed, so that the installation of the rear supporting structure is difficult, and the installation efficiency of the engine is low.
In view of the above-mentioned technologies, the prior art with the publication number CN217452837U provides a solution, but the structure is complex, and the actual implementation of the structural flexibility depends on the gap between the inner circumferential surface of the limit fixing ring and the outer circumferential surface of the support pin, but the gap can cause the limit fixing ring and the support pin to generate collision friction, so that the limit fixing ring and the support pin can generate loss in the user, and the service life of the component is further affected, and therefore, a better technical scheme is required to avoid the drawbacks existing in the prior art.
Disclosure of Invention
The invention aims to provide a self-adaptive fixing pin mounting device for an aircraft engine, which is used for solving the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
the self-adaptive fixing pin device for mounting the aero-engine comprises a supporting pin and a supporting head, wherein a limiting fixing ring is sleeved on the supporting pin, and at least three movable balls are embedded in one end, facing the supporting head, of the limiting fixing ring; the end, facing the limiting fixing ring, of the support head is provided with at least three clamping grooves, a movable auxiliary part is clamped in each clamping groove, an arc-shaped groove is formed in one end, facing the limiting fixing ring, of each movable auxiliary part, one end, facing the support head, of each movable ball is arranged in one arc-shaped groove in a matched mode, and when one end of each movable ball is arranged in the arc-shaped groove in a matched mode, a movable gap is formed between the support head and the limiting fixing ring; every activity ball all can dismantle with supporting the head through the connecting piece and be connected, and every activity ball all passes a activity auxiliary member.
As a preferable technical scheme, the limiting fixing ring comprises two semicircular hoops, one surfaces of the two semicircular hoops, which face the supporting pin, are respectively provided with a U-shaped groove, and the two semicircular hoops are connected through bolts and are sleeved on the flange of the supporting pin.
As a preferred technical solution in the present invention, a rectangular limiting protrusion is disposed at the other end of the movable auxiliary member, a rectangular limiting portion is disposed at the bottom of the clamping groove, and the rectangular limiting protrusion is disposed in the rectangular limiting portion in a matching manner.
As a preferable technical scheme in the invention, the opening end of the clamping groove and the edge of the supporting head are chamfered.
As a preferable technical solution of the present invention, the connecting member is a bolt, and a screw portion of the bolt passes through the movable auxiliary member and is in threaded connection with the corresponding movable ball.
As a preferable technical solution of the present invention, the connecting member is screwed with the movable auxiliary member.
As a preferable technical solution in the present invention, a washer is disposed between the nut end of the connecting member and the support head.
As a preferred technical solution in the present invention, the connecting member 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 member and one end of the support head and is connected with the nut.
As a preferable technical solution of the present invention, a washer is provided between the nut and the support head.
As a preferable technical scheme, the support head is externally connected with a bearing, an inner ring of the bearing is fixedly connected with the support head, and the connecting piece is connected with an outer ring of the bearing.
Has the beneficial effects that: the limit fixing ring is sleeved outside the supporting pin, so that the supporting pin and the limit fixing ring can rotate relatively, the flexibility and the self-adaptive capacity of the device for adaptively installing the fixing pin of the aero-engine are improved through the rotating relation, the supporting head is in contact with a movable spherical surface on the supporting pin through the movable auxiliary part, when the supporting head and the supporting pin need to be adjusted, the movable ball can enable the supporting head and the supporting pin to change at a certain angle, the movable gap is a movable space with the angle change, the supporting head and the supporting pin can move in a small range, the size interference of the aero-engine during installation is avoided, the phenomenon of different forces at the front and rear mounting points of the aero-engine is prevented, the processing difficulty of the size of a bracket of the aero-engine is reduced, and the installation efficiency of the aero-engine is effectively improved; the movable auxiliary part is clamped in the clamping groove of the supporting head, so that the movable auxiliary part can be replaced according to actual conditions, the stability and flexibility of the structure can be controlled under the optimal condition, the stability of the movable auxiliary part can be ensured when the movable auxiliary part is assembled in the clamping groove, one end of each movable auxiliary part, which faces the limiting fixing ring, is provided with an arc-shaped groove, one end of each movable ball, which faces the supporting head, is arranged in one arc-shaped groove in a matched manner, so that the movable auxiliary part is in surface contact with the movable ball, the structural stability during contact is ensured, and the damage of point contact to equipment is avoided; every movable ball all can dismantle with supporting the head through the connecting piece and be connected, and every movable ball all passes a activity auxiliary member, and then guarantees that the supporting pin can guarantee again to support the head when keeping certain home range to be connected steadily between the two, and then guarantees that the supporting pin is adjustable with the stability of supporting the head.
Drawings
Fig. 1 is a schematic view of the connection structure of the present invention.
In the figure: 1-a support pin; 101-a flange; 2-a support head; 3-limiting a fixing ring; 4-a movable ball; 5-a mobility aid; 6-connecting piece; 7-washer.
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 embodiments or the description in the prior art, 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 by those skilled in the art without creative efforts. It should be noted that the description of the embodiments is provided to help understanding of the present invention, and the present invention is not limited thereto.
The first embodiment is as follows:
as shown in fig. 1, the embodiment provides a self-adaptive fixed pin installation device for an aircraft engine, which includes a support pin 1 and a support head 2, wherein a limiting fixing ring 3 is sleeved outside the support pin 1, so that the support pin 1 and the limiting fixing ring 3 can rotate relatively, and further the flexibility and the self-adaptive capability of the self-adaptive fixed pin installation device for the aircraft engine are improved through the rotation relationship, at least three movable balls 4 are embedded in one end of the limiting fixing ring 3 facing the support head 2, the three movable balls 4 can rotate freely at one end of the limiting fixing ring 3 facing the support head 2, and all the movable balls 4 are preferably arranged on the limiting fixing ring 3 in an evenly distributed manner, so as to ensure the structural stability during later connection and use; at least three clamping grooves are arranged at one end of the supporting head 2 facing the limiting fixing ring 3, a movable auxiliary part 5 is clamped in each clamping groove, the movable auxiliary parts 5 can be assembled and disassembled through the clamping grooves, and then the movable auxiliary parts 5 can be replaced according to actual conditions so as to ensure that the stability and flexibility of the structure can be controlled under the best condition (for example, the structural sizes of two movable auxiliary parts 5 in the figure 1 are different, and when the size difference is large enough, the stability and flexibility of the structure can be properly influenced), when the movable auxiliary parts 5 are assembled in the clamping grooves, the stability of the movable auxiliary parts 5 can be ensured, one end of each movable auxiliary part 5 facing the limiting fixing ring 3 is provided with an arc-shaped groove, one end of each movable ball 4 facing the supporting head 2 is arranged in one arc-shaped groove in a matching way, further keeping the movable auxiliary part 5 in surface contact with the movable ball 4, further ensuring the structural stability during contact, avoiding the damage of point contact to equipment, and when one end of the movable ball 4 is arranged in the arc groove in a matching way, a movable gap is arranged between the support head 2 and the limiting fixing ring 3, the support head 2 is in surface contact with the movable ball 4 through the movable auxiliary part 5, when the support head 2 and the support pin 1 need to be adjusted, the movable ball 4 can make a certain angle change between the support head 2 and the support pin 1, and the movable gap is a movable space with the angle change, further making the support head 2 and the support pin 1 have small-range movement, further avoiding the size interference of an aeroengine during installation, preventing the phenomenon of other forces from occurring at the front and back mounting points of the aeroengine, and reducing the processing difficulty of the bracket size of the aeroengine, thereby effectively improving the installation efficiency of the aircraft engine; every movable ball 4 all can dismantle through connecting piece 6 with supporting head 2 and be connected, and every movable ball 4 all passes a activity auxiliary 5, and then guarantees that support pin 1 and support head 2 can guarantee stable connection between the two again when keeping certain home range, and then guarantees that the stability of support pin 1 and support head 2 is adjustable.
The limiting fixing ring 3 is sleeved outside the supporting pin 1, so that the supporting pin 1 and the limiting fixing ring 3 can rotate relatively, the flexibility and the self-adaptive capacity of the self-adaptive fixing pin installation device of the aero-engine are improved through the rotating relation, the supporting head 2 is in surface contact with the movable ball 4 on the supporting pin 1 through the movable auxiliary part 5, when the supporting head 2 and the supporting pin 1 need to be adjusted, the movable ball 4 can enable the supporting head 2 and the supporting pin 1 to change a certain angle, the movable gap is a movable space with the changed angle, and small-range movement is achieved between the supporting head 2 and the supporting pin 1, so that size interference of the aero-engine during installation is avoided, the phenomenon that the front and rear mounting points of the aero-engine are not rigid is avoided, the processing difficulty of the size of an aero-engine bracket is reduced, and the installation efficiency of the aero-engine is effectively improved; the movable auxiliary part 5 is clamped in the clamping groove of the support head 2, so that the movable auxiliary part 5 can be replaced according to actual conditions, the stability and flexibility of the structure can be controlled under the optimal condition, when the movable auxiliary part 5 is assembled in the clamping groove, the stability of the movable auxiliary part 5 can be ensured, one end of each movable auxiliary part 5, facing the limiting fixing ring 3, is provided with an arc-shaped groove, one end of each movable ball 4, facing the support head 2, is arranged in one arc-shaped groove in a matched mode, so that the movable auxiliary part 5 and the movable balls 4 are in surface contact, the structural stability during contact is ensured, and the equipment is prevented from being damaged by point contact; every movable ball 4 all can dismantle with supporting head 2 through connecting piece 6 and be connected, and every movable ball 4 all passes a activity auxiliary member 5, and then guarantees that support pin 1 and support head 2 can guarantee the stable connection between the two again when keeping certain home range, and then guarantees that the stability of support pin 1 and support head 2 is adjustable.
As a preferred embodiment in this embodiment, it should be further noted that the limit fixing ring 3 includes two semicircular clips, one surface of each of the two semicircular clips facing the support pin 1 is provided with a U-shaped groove, and the two semicircular clips are connected to the flange 101 of the support pin 1 through bolts and are sleeved on the flange 101, so that the limit fixing ring 3 can be installed without damaging the structure of the support pin 1, and the limit fixing ring 3 can also rotate on the flange 101 of the support pin 1, thereby improving the flexibility between the support head 2 and the support pin 1.
As a preferred embodiment in this embodiment, it should be further explained that the other end of the movable auxiliary part 5 is provided with a rectangular limiting protrusion, the bottom of the clamping groove is a rectangular limiting portion, the rectangular limiting protrusion is matched with the rectangular limiting portion, and the movable auxiliary part 5 is more stable after being installed due to the matching of the rectangular limiting protrusion and the rectangular limiting portion, so that the connecting part 6 is easier and more convenient to install.
As a preferred embodiment in this embodiment, it should be further described that the opening end of the clamping groove and the edge of the supporting head 2 are both arranged in a chamfered manner, the chamfered arrangement can avoid the occurrence of collision damage caused by contact at the corner position, and further makes the structural stability better, and meanwhile, the supporting head 2 after being chamfered is combined, when the supporting head 2 is adjusted relative to the supporting pin 1, if the supporting head 2 contacts the supporting pin 1, the adjustment of the supporting head 2 can be more natural, the collision at the corner position is avoided, and meanwhile, the chamfer at the corner position can also avoid more adjusting spaces, and further improves the flexibility.
As a preferred embodiment in this embodiment, it should be further described that the connecting member 6 is a bolt, and a screw portion of the bolt passes through the movable auxiliary member 5 and is in threaded connection with the corresponding movable ball 4, so that the connection manner is convenient, and the structural stability is good.
As a preferred embodiment in this embodiment, it should be further explained that the connecting member 6 is screwed with the movable auxiliary member 5, so as to further enhance the stability of the movable auxiliary member 5, and since the movable auxiliary member 5 is clamped on the supporting head 2, the screwed connection between the connecting member 6 and the movable auxiliary member 5 is also convenient.
As a preferred embodiment in this embodiment, it should be further explained that a washer 7 is disposed between the nut end of the connecting member 6 and the supporting head 2, so as to reduce wear and ensure the service life of the device.
Example two:
the present embodiment is a further improvement on the basis of the first embodiment, and specific differences between the present embodiment and the first embodiment are as follows:
as a preferred embodiment of the present invention, it should be further explained 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, and the other end of the screw sequentially passes through the movable auxiliary member 5 and one end of the support head 2 and is connected with the nut, so that the connection of the connecting member 6 is more convenient and stable.
As a preferred embodiment in this embodiment, it should be further noted that a washer is disposed between the nut and the support head 2, so as to reduce wear and ensure the service life of the device.
Example three:
the present embodiment is a further improvement 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 described that a bearing is connected outside the support head 2, an inner ring of the bearing is fixedly connected to the support head 2, and the connecting member 6 is connected to an outer ring of the bearing, so as to avoid rotation between the limit fixing ring 3 and the support pin 1, further reduce loss of the limit fixing ring 3 and the support pin 1, and ensure a service life of the device.
Finally, it should be noted that: the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The self-adaptive fixed pin mounting device for the aircraft 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 in one end, facing the supporting head (2), of the limiting fixing ring (3); the supporting head (2) is provided with at least three clamping grooves towards one end of the limiting fixing ring (3), a movable auxiliary part (5) is clamped in each clamping groove, an arc-shaped groove is formed in one end of each movable auxiliary part (5) towards the limiting fixing ring (3), one end of each movable ball (4) towards the supporting 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 supporting head (2) and the limiting fixing ring (3); every activity ball (4) all can be dismantled with supporting head (2) through connecting piece (6) and be connected, and every activity ball (4) all passes a activity auxiliary member (5).
2. An aircraft engine adaptive installation fixing pin device according to claim 1, characterized in that the limiting fixing ring (3) comprises two semicircular hoops, one side of each semicircular hoop facing the supporting pin (1) is provided with a U-shaped groove, and the two semicircular hoops are connected through bolts and sleeved on the flange (101) of the supporting pin (1).
3. An aircraft engine self-adaptive mounting fixing pin device according to claim 1, characterized in that the other end of the movable auxiliary member (5) is provided with a rectangular limiting protrusion, the bottom of the clamping groove is a rectangular limiting part, and the rectangular limiting protrusion is arranged in the rectangular limiting part in a matching manner.
4. An aircraft engine adaptive installation 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 chamfered.
5. An aircraft engine adaptive installation fixing pin device according to claim 1, characterized in that the connecting piece (6) is a bolt, the screw part of which passes through the movable auxiliary piece (5) and is in threaded connection with the corresponding movable ball (4).
6. An aeroengine adaptive installation fixing pin apparatus according to claim 5, wherein the connecting member (6) is threadedly connected to the mobility assistance member (5).
7. An aeroengine adaptive installation fixing pin arrangement according to claim 5, wherein a washer (7) is provided between the nut end of the connector (6) and the support head (2).
8. An aeroengine self-adaptive installation fixing pin device according to claim 1, wherein the connecting piece (6) is a screw, one end of the screw is integrally formed or in threaded connection with the movable ball (4), and the other end of the screw sequentially penetrates through the movable auxiliary piece (5) and one end of the support head (2) and is connected with a nut.
9. An aeroengine adaptive installation fixation pin arrangement according to claim 8, wherein a washer is provided between the nut and the support head (2).
10. An aeroengine adaptive installation fixing pin device according to any one of claims 1-9, wherein a bearing is connected outside the support head (2), the inner ring of the bearing is fixedly connected with the support head (2), and the connecting piece (6) is connected with 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 |
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| Publication Number | Publication Date |
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| CN115890179A true CN115890179A (en) | 2023-04-04 |
| CN115890179B CN115890179B (en) | 2023-09-26 |
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| CN202211461070.8A Active CN115890179B (en) | 2022-11-21 | 2022-11-21 | Self-adaptive fixing pin installation device for aero-engine |
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| CN115890179B (en) | 2023-09-26 |
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