CN217452837U - 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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- CN217452837U CN217452837U CN202222103636.1U CN202222103636U CN217452837U CN 217452837 U CN217452837 U CN 217452837U CN 202222103636 U CN202222103636 U CN 202222103636U CN 217452837 U CN217452837 U CN 217452837U
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- pin
- ring
- joint bearing
- fixing
- supporting
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- 238000009434 installation Methods 0.000 claims abstract description 25
- 239000007787 solid Substances 0.000 claims abstract description 9
- 230000003044 adaptive effect Effects 0.000 claims 4
- 230000000694 effects Effects 0.000 abstract description 3
- 238000005299 abrasion Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 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
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The utility model relates to an aeroengine installs technical field, in particular to aeroengine self-adaptation installation fixed pin device, including supporting pin and support head, supporting pin and support head are through inner structure swing joint in order to realize along the axis rotation and the universal rotation activity of small angle, inner structure includes joint bearing, spacing solid fixed ring and spacing subassembly, the front end of supporting pin is pegged graft in joint bearing, joint bearing embeds in the support head, the spacing subassembly is spacing to joint bearing, spacing solid fixed ring overcoat is in the supporting pin and is connected with the support head; the utility model provides a structural design is simple, can the self-adaptation installation aeroengine, aeroengine self-adaptation installation fixed pin device that the installation effectiveness is high.
Description
Technical Field
The utility model relates to an aeroengine installation technical field, in particular to aeroengine self-adaptation installation fixed pin device.
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 and a bracket are assembled, two solid integrated fixing pins are generally used at the front part of the aero-engine, the mounting mode is easy to cause uneven stress and size interference, and the requirement on processing the size of a fixing pin support piece is high. In addition, after the front part of the aero-engine is fixed, a phenomenon of stiffness 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.
SUMMERY OF THE UTILITY MODEL
The utility model aims at overcoming the defect and not enough that prior art exists, providing a structural design is simple, can the self-adaptation installation aeroengine, aeroengine self-adaptation installation fixed pin device that the installation effectiveness is high.
Realize the utility model discloses the technical scheme of purpose is: the utility model provides an aeroengine self-adaptation installation fixed pin device, includes the supporting pin and supports the head, the supporting pin passes through inner structure swing joint with supporting the head to realize along the axis rotation with the universal rotatory activity of small angle, inner structure includes joint bearing, spacing solid fixed ring and spacing subassembly, the front end of supporting pin is pegged graft in joint bearing, joint bearing is embedded in supporting the head, spacing subassembly is spacing to joint bearing, spacing solid fixed ring overcoat in the supporting pin and with support the head and be connected.
Furthermore, the limiting assembly comprises a front pressing piece and a rear pressing piece, and the front pressing piece and the rear pressing piece respectively press the front side and the rear side of the knuckle bearing.
Further, the front pressing piece comprises a pressing fixing ring and a pressing screw, and the pressing fixing ring is mounted at the front end of the supporting pin through the pressing screw and presses the front end of the joint bearing inner ring.
Furthermore, the rear pressing piece comprises a limiting ring and a pressing fixing nut, and the limiting ring and the pressing fixing nut press the rear end of the outer ring of the joint bearing.
Furthermore, the limiting fixing ring is composed of two fixing half rings, steps are arranged on the inner circumferential edge of each fixing half ring, and the steps limit the flanges on the supporting pins.
After the technical scheme is adopted, the utility model discloses following positive effect has:
(1) the utility model has the advantages that through the arrangement of the internal structure, a small range of movement is formed between the supporting pin and the supporting head, so that the size interference of the aero-engine during the 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 the aero-engine bracket is reduced, and the installation efficiency of the aero-engine is effectively improved;
(2) the utility model discloses well spacing solid fixed ring comprises two stationary half rings to the installation of cup jointing of spacing solid fixed ring of being convenient for.
Drawings
In order that the present invention may be more readily and clearly understood, the following detailed description of the present invention is given in conjunction with the accompanying drawings, in which:
fig. 1 is a schematic structural view of the present invention;
fig. 2 is an exploded view of the present invention;
fig. 3 is a cross-sectional view of the present invention;
FIG. 4 is a schematic view of the steps of the present invention;
fig. 5 is an enlarged view of a portion a in fig. 3.
In the figure: the support pin 1, the flange 11, the support head 2, the joint bearing 31, the limit fixing ring 32, the fixing half ring 321, the step 3211, the limit component 33, the front pressing member 331, the pressing fixing ring 3311, the pressing screw 3312, the spring washer 3313, the rear pressing member 332, the limit ring 3321, the pressing fixing nut 3322, the connecting bolt 4, the lock nut 5, the washer 6, and the gap 7.
Detailed Description
As shown in fig. 1-5, an aeroengine self-adaptation installation fixed pin device, including supporting pin 1 and support head 2, supporting pin 1 and support head 2 pass through inner structure swing joint, through inner structure's setting for there is the activity of minizone between supporting pin 1 and the support head 2, and then avoid aeroengine size to interfere when the installation, prevent that aeroengine front and back mounting point from appearing other strong phenomenon, reduce the processing degree of difficulty of aeroengine bracket size, thereby effectively improved aeroengine's installation effectiveness. Specifically, the internal structure includes a joint bearing 31, a limiting fixing ring 32 and a limiting component 33, the front end of the supporting pin 1 is inserted into the joint bearing 31, the joint bearing 31 is embedded in the supporting head 2, the limiting component 33 limits the joint bearing 31 to keep the stability of the joint bearing 31, and the limiting fixing ring 32 is sleeved outside the supporting pin 1 and connected with the supporting head 2. Note that, the limit fixing ring 32 is not sleeved on the support pin 1, but the support pin 1 is not locked, and a gap 7 is formed between the inner circumferential surface of the limit fixing ring 32 and the outer circumferential surface of the support pin 1, so that the support head 2 can realize a small-angle universal rotational movement through the joint bearing 31. The limiting component 33 comprises a front pressing piece 331 and a rear pressing piece 332, and the front pressing piece 331 and the rear pressing piece 332 respectively press the front side and the rear side of the knuckle bearing 31. The front pressing member 331 includes a pressing fixing ring 3311 and a pressing screw 3312, the pressing fixing ring 3311 is mounted on the front end of the support pin 1 by the pressing screw 3312 and presses the front end of the inner race of the joint bearing 31, and a spring washer 3313 is provided between the pressing fixing ring 3311 and the pressing screw 3312. The rear pressing member 332 includes a limit ring 3321 and a pressing fixing nut 3322, the limit ring 3321 and the pressing fixing nut 3322 press the rear end of the outer ring of the joint bearing 31, and the pressing fixing nut 3322 is provided between the limit ring 3321 and the joint bearing 31. The limit fixing ring 32 is composed of two fixing half rings 321, so that the jacket installation of the limit fixing ring 32 is facilitated, steps 3211 are arranged on the inner circumferential edges of the two fixing half rings 321, and the steps 3211 limit the flange 11 on the support pin 1, so that the movable range of the support head 2 is limited. The limit fixing ring 32 is connected with the support head 2 through the connecting bolt 4 and the locking nut 5, and a gasket 6 is arranged between the limit fixing ring 32 and the support head 2 in order to avoid rigid abrasion between the limit fixing ring 32 and the support head 2.
In practical application, the left part and the right part of the front part of the aero-engine are respectively connected with a set of the device, the supporting head 2 is connected with a supporting point interface of the aero-engine, and the aero-engine and the supporting pin 1 fall on an engine bracket together. The supporting pin 1 and the supporting head 2 can rotate along the axis by matching the outer ring and the inner ring of the inner structure joint bearing 31, and can realize small-angle universal rotation, so that the aero-engine has a certain degree of freedom on the bracket, difficulty and interference are avoided when the supporting frame at the rear part of the bracket is installed, and meanwhile, the phenomenon of stiffness of the front and rear mounting points of the aero-engine is avoided, thereby greatly improving the installation efficiency of the engine.
The above-mentioned embodiments, further detailed description of the objects, technical solutions and advantages of the present invention, it should be understood that the above description is only the embodiments of the present invention, and is not intended to limit the present invention, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (5)
1. The utility model provides an aeroengine self-adaptation installation fixed pin device, includes supporting pin (1) and support head (2), its characterized in that: the supporting pin (1) and the supporting head (2) are movably connected through an internal structure to achieve universal rotation and movement along the axis in a small angle mode, the internal structure comprises a joint bearing (31), a limiting fixing ring (32) and a limiting component (33), the front end of the supporting pin (1) is connected to the joint bearing (31) in an inserting mode, the joint bearing (31) is embedded into the supporting head (2), the limiting component (33) is limited to the joint bearing (31), and the limiting fixing ring (32) is sleeved on the supporting pin (1) and connected with the supporting head (2).
2. An aircraft engine adaptive installation fixing pin arrangement according to claim 1, characterised in that: the limiting assembly (33) comprises a front pressing piece (331) and a rear pressing piece (332), and the front pressing piece (331) and the rear pressing piece (332) respectively press the front side and the rear side of the knuckle bearing (31).
3. An aircraft engine adaptive installation fixing pin arrangement according to claim 2, characterised in that: preceding pressing member (331) including compress tightly solid fixed ring (3311) and housing screw (3312), compress tightly solid fixed ring (3311) and install the front end at supporting pin (1) and compress tightly the front end of joint bearing (31) inner circle through housing screw (3312).
4. An aircraft engine adaptive installation fixing pin arrangement according to claim 2, characterised in that: the rear pressing piece (332) comprises a limiting ring (3321) and a pressing fixing nut (3322), and the limiting ring (3321) and the pressing fixing nut (3322) press the rear end of the outer ring of the knuckle bearing (31).
5. An aeroengine adaptive installation fixing pin apparatus according to claim 3 or 4, characterised in that: the limiting fixing ring (32) is composed of two fixing half rings (321), steps (3211) are arranged on the inner circle periphery of each fixing half ring (321), and the steps (3211) limit the flange (11) on the support pin (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222103636.1U CN217452837U (en) | 2022-08-11 | 2022-08-11 | Self-adaptive mounting fixing pin device for aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222103636.1U CN217452837U (en) | 2022-08-11 | 2022-08-11 | Self-adaptive mounting fixing pin device for aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217452837U true CN217452837U (en) | 2022-09-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222103636.1U Active CN217452837U (en) | 2022-08-11 | 2022-08-11 | Self-adaptive mounting fixing pin device for aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217452837U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115890179A (en) * | 2022-11-21 | 2023-04-04 | 成都环泰睿诚科技有限公司 | Self-adaptive mounting fixing pin device for aero-engine |
-
2022
- 2022-08-11 CN CN202222103636.1U patent/CN217452837U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115890179A (en) * | 2022-11-21 | 2023-04-04 | 成都环泰睿诚科技有限公司 | Self-adaptive mounting fixing pin device for aero-engine |
| CN115890179B (en) * | 2022-11-21 | 2023-09-26 | 成都环泰睿诚科技有限公司 | Self-adaptive fixing pin installation device for aero-engine |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: Room 303-19, No. 333 Huanhu West 1st Road, Nanhui New Town, Pudong New Area, Shanghai, 200120 Patentee after: Shanghai Shangfei Aircraft Equipment Manufacturing Co.,Ltd. Address before: Room 303-19, No. 333 Huanhu West 1st Road, Nanhui New Town, Pudong New Area, Shanghai, 200120 Patentee before: SHANGHAI SHANGFEI AIRCRAFT EQUIPMENT MANUFACTURING Co.,Ltd. |