CN208761993U - A kind of aircraft engine axial workpiece hanger structure - Google Patents
A kind of aircraft engine axial workpiece hanger structure Download PDFInfo
- Publication number
- CN208761993U CN208761993U CN201820892363.4U CN201820892363U CN208761993U CN 208761993 U CN208761993 U CN 208761993U CN 201820892363 U CN201820892363 U CN 201820892363U CN 208761993 U CN208761993 U CN 208761993U
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- Prior art keywords
- calvus
- rod
- aircraft engine
- arc
- axial workpiece
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Abstract
The utility model provides a kind of aircraft engine axial workpiece hanger structure comprising: calvus installing component has two calvus fixed parts, and it is in X-shaped that two calvus fixed parts, which intersect, and intersection and the first installation axle are hinged；Calvus component comprising two arc calvus being oppositely arranged, arc calvus are fixedly installed on calvus fixed part；Limiting component, it includes position-limited claw, position-limited claw includes first body of rod, first body of rod has opposite first end and the second end, bending forms second body of rod at first end, and bending forms raised line at the second end, and first body of rod, second body of rod and raised line constitute zigzag position-limited claw, bending part between first body of rod and second body of rod is articulated on calvus installing component, and the end of raised line extends to the surface of the first installation axle.The utility model is adapted to the limit of complicated claw construction compared to the prior art, more convenient to mounting, commissioning and maintenance calvus and position limiting structure.
Description
Technical field
The utility model relates to a kind of aircraft engine axial workpiece lifting devices, send out in particular to a kind of aircraft
Motivation axial workpiece hanger structure.
Background technique
When for the processing of axial workpiece used in aircraft engine, need to complete lifting operation using suspender.
Traditional suspender is mainly made of multiple calvus and mounting rod and limiting component, and two arc calvus institutes are normally comprised
Composition, and this kind of calvus also needs to carry out encapsulated processing, is limited in calvus moving process by limiting component.
In traditional technology, by being realized limit to calvus on the outside, but be directed in the upper installation body of rod such as mounting rod
Some more complicated claw constructions of structure, such as the claw construction of X-shaped certainly will need to install the more body of rod and just be able to achieve limit
No matter position effect is being installed or is being used in the maintenance in later period in other words, all more troublesome.
Utility model content
In consideration of it, the utility model provides a kind of aircraft engine arbor class zero for being adapted to complicated claw construction limit
Part hanger structure.
For this purpose, the utility model provides a kind of aircraft engine axial workpiece hanger structure comprising:
Calvus installing component has two calvus fixed parts, and it is in X-shaped, intersection and first that two calvus fixed parts, which intersect,
Installation axle is hinged；
Calvus component comprising an at least calvus group, calvus group include two arc calvus being oppositely arranged, on arc calvus
It is coated with glue-line, arc calvus is fixedly installed on calvus fixed part；
Limiting component comprising position-limited claw, position-limited claw include first body of rod, first body of rod have opposite first end and
The second end, bending forms second body of rod at first end, and bending forms raised line, first body of rod, second body of rod at the second end
Zigzag position-limited claw is constituted with raised line, the bending part between first body of rod and second body of rod is articulated on calvus installing component, raised line
End extend to the surface of the first installation axle, the first gag lever post with the cooperation of calvus installing component is provided on second body of rod,
The second gag lever post with position-limited claw cooperation is provided on calvus installing component.
Further, the third end of above-mentioned calvus fixed part forms the curved region of arc, opposite third end on calvus fixed part
The 4th hinged mounting plate in end in portion, hinged by the second installation axle between the end of two mounting plates, first body of rod and the second bar
Bending part between body is articulated in the second installation axle.
Further, fixation is equipped with more support rods on the curved region of above-mentioned arc, and the end of support rod is fixedly connected with arc
Calvus.
Further, on region of above-mentioned second gag lever post between third end and the 4th end.
Further, the width of above-mentioned first body of rod gradually broadens from first end to the second end.
Further, above-mentioned second body of rod is V shape pole body.
Further, above-mentioned first gag lever post is installed on the bending part on second body of rod.
Further, above-mentioned arc calvus is made of disc, offers on disc and the body concentric circular hole of disk, circle
It is coated with glue-line on disk body, two cutting line components being oppositely arranged are provided on disc, it is in eight that cutting line component, which includes two,
First cutting line of font arrangement, the first cutting line are radially extended along disc, and one end of the first cutting line extends to circle
The other end of the hole Yan Chu in hole, the first cutting line connect the second cutting line, and the free end of the second cutting line extends to disc
Edge, forms angle between the second cutting line and the first cutting line, the region between two cutting line components cuts to form arc pawl
Piece.
A kind of aircraft engine axial workpiece hanger structure provided by the utility model, leads compared to the prior art
Have the advantage that the structure design using the position-limited claw of zigzag structure, one end and the hinged place of two mounting plates are cut with scissors
It connecing, the hinged place of the other end and two calvus carries out limit cooperation, adapt to the calvus mounting structure of this kind of double X shape structures, and with
The folding of claw construction carry out the variation of position, to be conducive to realize limit to the folding angle of the hinged place of calvus, thus
It effectively utilizes a position limiting structure to limit X-shaped claw construction, adapts to the limit of complicated claw construction, to installing, make
With with maintenance calvus and position limiting structure it is more convenient.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field
Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as practical to this
Novel limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is a kind of aircraft engine axial workpiece hanger structure provided by the embodiment of the utility model in front viewing angle
Under structural schematic diagram；
Fig. 2 is a kind of aircraft engine axial workpiece hanger structure provided by the embodiment of the utility model in side view angle
Under structural schematic diagram；；
Fig. 3 is limiting component in a kind of aircraft engine axial workpiece hanger structure provided by the embodiment of the utility model
Structural schematic diagram；
Fig. 4 is disc in a kind of aircraft engine axial workpiece hanger structure provided by the embodiment of the utility model
Structural schematic diagram.
Specific embodiment
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
It is fully disclosed to those skilled in the art.
Embodiment one:
Referring to Fig. 1 to Fig. 3, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment one is shown in figure
With hanger structure comprising: calvus installing component 1 has two calvus fixed parts 11, and it is in X-shaped that two calvus fixed parts 11, which intersect,
Intersection and the first installation axle 12 are hinged；Calvus component 2 comprising two calvus groups 21 (also can according to need setting multiple groups
Or only one group), calvus group 21 includes two arc calvus 22 being oppositely arranged, and is coated with glue-line 23, arc on arc calvus 22
Calvus 22 is fixedly installed on calvus fixed part 11；Limiting component 3 comprising position-limited claw 31, position-limited claw 31 include first body of rod
32, first body of rod 32 has opposite first end 321 and the second end 322, and bending forms second body of rod at first end 321
33, bending forms raised line 34 at the second end 322, and first body of rod 32, second body of rod 33 and raised line 34 constitute zigzag position-limited claw,
Bending part between first body of rod 32 and second body of rod 33 is articulated on calvus installing component 1, and the end of raised line 34 is pacified to first
The surface for filling axis 12 extends, and the first gag lever post 35 cooperated with calvus installing component 1, calvus installation are provided on second body of rod 33
The second gag lever post 36 cooperated with position-limited claw 31 is provided on component 1.
A kind of aircraft engine axial workpiece hanger structure, main compared to the prior art provided by the present embodiment
It having the advantage that and is designed using the structure of the position-limited claw of zigzag structure, the hinged place of one end and two mounting plates carries out hingedly,
The hinged place of the other end and two calvus carries out limit cooperation, adapts to the calvus mounting structure of this kind of double X-shaped structures, and with pawl
The folding of chip architecture carries out the variation of position, to be conducive to realize limit to the folding angle of the hinged place of calvus, thus effectively
Ground limits X-shaped claw construction using a position limiting structure, adapts to the limit of complicated claw construction, to installation, using and
Safeguard that calvus and position limiting structure are more convenient.
Embodiment two:
Referring to Fig. 1 to Fig. 3, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment two is shown in figure
With hanger structure, the present embodiment is also further made that following as improved technical side on the basis of the above embodiments
Case: the third end 13 of calvus fixed part 11 forms the curved region 131 of arc, with respect to the 4th of third end 13 on calvus fixed part 11
The hinged mounting plate 15 in end 14, hinged by the second installation axle 151 between the end of two mounting plates 15, first body of rod 32 and second
Bending part between the body of rod 33 is articulated in the second installation axle 151；Fixation is equipped with more support rods 16 on the curved region 131 of arc,
The end of support rod 16 is fixedly connected with arc calvus 22.By the setting of above structure, the installation of calvus can be made more steady
Gu.
Embodiment three:
Referring to Fig. 1 to Fig. 3, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment three is shown in figure
With hanger structure, the present embodiment is also further made that following as improved technical side on the basis of the above embodiments
Case: the second gag lever post 36 is on the region between third end 13 and the 4th end 14.It, can be with by the setting of above structure
The limit to position-limited claw is formed in the best balanced point of application of position-limited claw, prevents position-limited claw opening and closing forces from spending and causes gag lever post greatly
Loose phenomenon is installed.
Example IV:
Referring to Fig. 1 to Fig. 3, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment four is shown in figure
With hanger structure, the present embodiment is also further made that following as improved technical side on the basis of the above embodiments
Case: the width of first body of rod 32 is gradually broadened from first end 321 to the second end 322.It, can be with by the setting of above structure
The more firm position-limited claw of structure is formed, and can use that tapered form makes can be with to the force dynamics of the second gag lever post
Reduce, guarantees the stability of the second gag lever post installation.
Embodiment five:
Referring to Fig. 1 to Fig. 3, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment five is shown in figure
With hanger structure, the present embodiment is also further made that following as improved technical side on the basis of the above embodiments
Case: second body of rod 33 is V shape pole body；First gag lever post 35 is installed on the bending part on second body of rod 33.Pass through above structure
Setting, can form the more firm position-limited claw of structure, and when position-limited claw is rotated as calvus opens and closes, and can be formed to the
The buffer function of one gag lever post guarantees the stability of the first gag lever post installation.
Embodiment six:
Referring to fig. 4, a kind of aircraft engine axial workpiece of the offer of the utility model embodiment six is shown in figure with hanging
Lamps structure, the present embodiment be also further made that on the basis of the above embodiments it is following as an improved technical scheme: arc
Shape calvus 22 is made of disc 4, and the circular hole 41 concentric with disc 4 is offered on disc 4, is coated with glue on disc 4
Layer 23, two cutting line components 42 being oppositely arranged are provided on disc 4, and cutting line component 42 includes two and arranges in splayed
The first cutting line 421, the first radially extending along disc 4 of cutting line 421, one end of the first cutting line 421 extends to
At 411, the other end of the first cutting line 421 connects the second cutting line 422 in the hole of circular hole 41, the second cutting line 422 from
The edge 43 of disc 4 is extended to by end, and included angle A, two cutting lines are formed between the second cutting line 422 and the first cutting line 421
It cuts to form arc calvus 22 in region between component 42.By the way that encapsulated layer is arranged on disk, and multiple cutting lines are set,
Can thus make disk may be implemented to be attached with the devices such as support rod and calvus fixing seat, then again to disk into
It goes and cuts, so that calvus completes installation after dicing, so that calvus is encapsulated more uniform, so that two arcs are encapsulated
Complete circle can be formed between pawl, effectively improve firm shape when calvus crawl axial workpiece.
Obviously, it is practical without departing from this can to carry out various modification and variations to the utility model by those skilled in the art
Novel spirit and scope.If in this way, these modifications and variations of the present invention belong to the utility model claims and
Within the scope of its equivalent technologies, then the utility model is also intended to include these modifications and variations.
Claims (8)
1. a kind of aircraft engine axial workpiece hanger structure characterized by comprising
Calvus installing component (1) has two calvus fixed parts (11), and it is in X-shaped that the two calvus fixed part (11), which is intersected, is intersected
It is hinged with the first installation axle (12) at point；
Calvus component (2) comprising an at least calvus group (21), the calvus group (21) include two arc calvus being oppositely arranged
(22), it is coated with glue-line (23) on the arc calvus (22), the arc calvus (22) is fixedly installed in the calvus and fixes
In portion (11)；
Limiting component (3) comprising position-limited claw (31), the position-limited claw (31) include first body of rod (32), first body of rod
(32) there is opposite first end (321) and the second end (322), bending forms the second bar at the first end (321)
Body (33), bending forms raised line (34) at the second end (322), first body of rod (32), second body of rod (33)
Zigzag position-limited claw is constituted with the raised line (34), the bending part between first body of rod (32) and second body of rod (33)
It being articulated on the calvus installing component (1), the end of the raised line (34) extends to the surface of first installation axle (12),
The first gag lever post (35) with the calvus installing component (1) cooperation, the calvus peace are provided on second body of rod (33)
The second gag lever post (36) with the position-limited claw (31) cooperation is provided on dress component (1).
2. a kind of aircraft engine axial workpiece hanger structure according to claim 1, which is characterized in that the calvus
The third end (13) of fixed part (11) forms the curved region of arc (131), the relatively described third end on the calvus fixed part (11)
The hinged mounting plate (15) in 4th end (14) in portion (13) passes through the second installation axle between the end of two mounting plates (15)
(151) hingedly, the bending part between first body of rod (32) and second body of rod (33) is articulated with second installation axle
(151) on.
3. a kind of aircraft engine axial workpiece hanger structure according to claim 2, which is characterized in that the arc is curved
Fixation is equipped with more support rods (16) on region (131), and the end of the support rod (16) is fixedly connected with the arc calvus
(22)。
4. a kind of aircraft engine axial workpiece hanger structure according to claim 2, which is characterized in that described second
Gag lever post (36) is on the region between the third end (13) and the 4th end (14).
5. a kind of aircraft engine axial workpiece hanger structure according to claim 1, which is characterized in that described first
The width of the body of rod (32) is gradually broadened by the first end (321) Xiang Suoshu the second end (322).
6. a kind of aircraft engine axial workpiece hanger structure according to claim 1, which is characterized in that described second
The body of rod (33) is V shape pole body.
7. a kind of aircraft engine axial workpiece hanger structure according to claim 6, which is characterized in that described first
Gag lever post (35) is installed on the bending part on second body of rod (33).
8. a kind of aircraft engine axial workpiece hanger structure according to claim 1, which is characterized in that the arc
Calvus (22) is made of disc (4), and the circular hole (41) concentric with the disc (4), institute are offered on the disc (4)
It states and is coated on disc (4) glue-line (23), two cutting line components being oppositely arranged are provided on the disc (4)
(42), the cutting line component (42) includes two the first cutting lines (421) in splayed arrangement, first cutting line
(421) one end of radially extending along the disc (4), first cutting line (421) extends to the circular hole (41)
Hole at (411), the other end of first cutting line (421) connects the second cutting line (422), second cutting line
(422) free end extends to the edge (43) of the disc (4), second cutting line (422) and first cutting
Angle (A) is formed between line (421), the region between the two cutting line components (42) cuts to form the arc calvus
(22)。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820892363.4U CN208761993U (en) | 2018-06-08 | 2018-06-08 | A kind of aircraft engine axial workpiece hanger structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820892363.4U CN208761993U (en) | 2018-06-08 | 2018-06-08 | A kind of aircraft engine axial workpiece hanger structure |
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| Publication Number | Publication Date |
|---|---|
| CN208761993U true CN208761993U (en) | 2019-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820892363.4U Expired - Fee Related CN208761993U (en) | 2018-06-08 | 2018-06-08 | A kind of aircraft engine axial workpiece hanger structure |
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| Country | Link |
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| CN (1) | CN208761993U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108584689A (en) * | 2018-06-08 | 2018-09-28 | 苏州市硕曜机械有限公司 | A kind of aircraft engine axial workpiece hanger structure |
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2018
- 2018-06-08 CN CN201820892363.4U patent/CN208761993U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108584689A (en) * | 2018-06-08 | 2018-09-28 | 苏州市硕曜机械有限公司 | A kind of aircraft engine axial workpiece hanger structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190419 Termination date: 20210608 |
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| CF01 | Termination of patent right due to non-payment of annual fee |