CN212552722U - Clamp for aero-engine case - Google Patents
Clamp for aero-engine case Download PDFInfo
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- CN212552722U CN212552722U CN202021231244.8U CN202021231244U CN212552722U CN 212552722 U CN212552722 U CN 212552722U CN 202021231244 U CN202021231244 U CN 202021231244U CN 212552722 U CN212552722 U CN 212552722U
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- positioning
- engine case
- positioning seat
- bulge
- clip
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Abstract
The utility model provides an anchor clamps for aeroengine machine casket, it can be used for clamping aeroengine machine casket to casket non-deformable in the course of working. The positioning seat is characterized by comprising a positioning seat, wherein the top of the positioning seat extends upwards to form a first bulge corresponding to the size of the large end of an engine case, an inner supporting column is connected to the middle of the positioning seat, the top of the inner supporting column is connected with a cover plate, and the cover plate extends downwards to form a second bulge corresponding to the size of the small end of the engine case; the positioning seat is also connected with a pressing plate, and the pressing plate is contacted with the outer side of the large end of the engine case; and the positioning seat is also provided with an anti-rotation hole, and the anti-rotation hole is connected with a positioning hole on the outer side of the large end of the engine case through a positioning pin.
Description
Technical Field
The utility model relates to a clamping anchor clamps technical field specifically is an anchor clamps for aeroengine machine casket.
Background
The engine case is provided with a plurality of cases on a new generation of aero-engine, such as an air inlet case, a culvert case, a fan case, a compressor case, a combustion chamber case, a turbine case and the like, wherein other parts can be welded on the cases to ensure the functions of the cases, the welding stress is released to cause the local deformation of the cases, so the precise sizes of assembling holes, flange mounting surfaces and the like on islands around the cases are all carried out after the welding of the cases is finished, the processing such as turning, multi-axis numerical control milling and the like is involved, most of the cases have thinner wall thickness, the cases are easily influenced by clamping force, cutting force and residual stress generated in the machining process to cause deformation in the machining process, the materials of the cases mostly adopt high-temperature alloy, titanium alloy and the like, the high-temperature alloy material is harder, the plastic deformation is large, the cutting force is large, the cutting temperature is high, the cutter is easy to wear, and the metallurgy of the cases are easy to, The manufacturing quality and performance level have a decisive influence on the improvement of the reliability, safety, service life and performance of the engine, and how to solve the problem of finish machining deformation of a complex welding casing is very important.
SUMMERY OF THE UTILITY MODEL
To the yielding problem of current aeroengine machine casket processing, the utility model provides an anchor clamps for aeroengine machine casket, it can be used for clamping aeroengine machine casket to casket non-deformable in the course of working.
The technical scheme is as follows: the utility model provides a anchor clamps for aeroengine machine casket, its includes the positioning seat, its characterized in that: the top of the positioning seat extends upwards to form a first bulge corresponding to the size of the large end of the engine case, an inner supporting column is connected in the middle of the positioning seat, the top of the inner supporting column is connected with a cover plate, and the cover plate extends downwards to form a second bulge corresponding to the size of the small end of the engine case; the positioning seat is also connected with a pressing plate, and the pressing plate is contacted with the outer side of the large end of the engine case; and the positioning seat is also provided with an anti-rotation hole, and the anti-rotation hole is connected with a positioning hole on the outer side of the large end of the engine case through a positioning pin.
It is further characterized in that:
the auxiliary support structure comprises a support part connected with the positioning seat, an inner support ring is connected onto the support part, and the top of the inner support ring is in contact with the bottom of an internal part of the engine case;
the lower end face of the inner support ring is provided with a connecting groove, and the support part extends into the connecting groove and is used for supporting the inner support ring;
the inner support ring comprises a shock-absorbing layer positioned at the top end;
the pressing plate is Z-shaped;
the top of the inner support column extends upwards to form a first positioning bulge, and a first positioning hole corresponding to the first positioning bulge is formed in the middle of the cover plate;
the bottom of the inner support column extends downwards to form a second positioning bulge, and a second positioning hole corresponding to the second positioning bulge is formed in the middle of the positioning seat;
the lower part of the inner support column is provided with a connecting part, and the connecting part is connected with the positioning seat through a connecting piece.
The utility model has the advantages that: when the clamping is carried out, the large end of the engine case can be arranged on the positioning seat corresponding to the first bulge, the positioning pin is used for connecting the anti-rotation hole in the positioning seat with the positioning hole in the outer side of the large end, the small end is compressed through the cover plate, the large end is compressed through the pressing plate to realize the clamping of the engine case, the first bulge on the positioning seat can support the large end from the inside to reduce the deformation of the large end during machining, and the second bulge on the cover plate can support the small end from the inside to reduce the deformation of the small end during machining.
Drawings
FIG. 1 is a view of the structure of the present invention;
FIG. 2 is a connection view of an anti-rotation hole and a positioning hole;
FIG. 3 is a top view of the positioning seat;
fig. 4 is a structural view of an inner support ring.
Detailed Description
As shown in fig. 1-3, the fixture for the aero-engine case comprises a positioning seat 1 connected with a machine tool, the top of the positioning seat 1 extends upwards to form a first bulge 1-1 corresponding to the size of the inner wall of the large end of an engine case 2, an inner support column 3 is connected in the middle of the positioning seat 1, the top of the inner support column 3 is connected with a circular cover plate 4, the cover plate 4 is connected with the inner support column 3 through a screw and tightly presses the small end of the engine case 2, the cover plate 4 extends downwards to form a second bulge 4-1 corresponding to the size of the inner wall of the small end of the engine case 2, and the cross section of the cover plate 4 is in a T shape; the positioning seat 1 is further connected with a plurality of Z-shaped pressing plates 5 through screws, the number of the Z-shaped pressing plates can be selected according to needs, for example, 16 pressing plates can be adopted, the problem that a main shaft of a peripheral island machine tool interferes with a clamp when a casing is machined is solved through Z shapes, and the pressing plates 5 are in contact with a large-end outward extending part of the engine casing 2 and are annularly distributed around the engine casing 2; with reference to fig. 2 and 3, the positioning seat 1 is further provided with an anti-rotation hole 1-2, and the anti-rotation hole 1-2 is connected with a positioning hole 2-1 on the outer side of the large end of the engine case 2 through a positioning pin 6.
During clamping, the first bulge 1-1 is used for positioning, the casing is prevented from moving through the positioning pin 6, the small end of the casing is pressed from the top through the cover plate 4, the large end of the casing is pressed from the periphery through the pressing plate 5 for clamping the casing, the first bulge 1-1 can be abutted against the large end from the inside to reduce the deformation of the large end during machining, the second bulge 4-1 on the cover plate 4 can be abutted against the small end from the inside to reduce the deformation of the small end during machining, and the extrusion deformation of parts under the cutting force during machining is effectively reduced.
With reference to fig. 4, the positioning seat further comprises an auxiliary supporting structure, the auxiliary supporting structure comprises a supporting part 6 connected with the positioning seat 1, the supporting part 6 is a stud, a plurality of supporting parts 6 are distributed annularly, an inner supporting ring 7 is connected to the upper part of the supporting part, and the top of the inner supporting ring 7 is in contact with the bottom of the inner part 2-2 of the engine case 2; specifically, the lower end face of the inner support ring 7 is provided with a connecting groove 7-1, and the support part 6 extends into the connecting groove 7-1 to support the inner support ring 7; the inner support ring 7 comprises a shock absorption layer 7-2 positioned at the top end, and the shock absorption layer 7-2 is a soft glue layer and is connected with the lower layer in an adhesion mode. Because the internal part 2-2 of the casing is heavier, the uncontrollable deformation caused by heavier mass and large machining allowance can be effectively relieved by arranging the internal support ring 7 to support the internal part, and meanwhile, the damping layer 7-2 can be used for buffering and damping to ensure the machining quality.
In order to facilitate installation and positioning, the top of the inner support column 3 extends upwards to form a first positioning bulge 3-1, and a first positioning hole corresponding to the first positioning bulge 3-1 is formed in the middle of the cover plate 4; the bottom of the inner support column 3 extends downwards to form a second positioning bulge 3-2, and a second positioning hole corresponding to the second positioning bulge 3-2 is formed in the middle of the positioning seat 1; meanwhile, the lower part of the inner support column 3 is provided with a connecting part 3-3, and the connecting part 3-3 is connected with the positioning seat 1 through a connecting piece such as a bolt.
The above description is only for the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides a anchor clamps for aeroengine machine casket, its includes the positioning seat, its characterized in that: the top of the positioning seat extends upwards to form a first bulge corresponding to the size of the large end of the engine case, an inner supporting column is connected in the middle of the positioning seat, the top of the inner supporting column is connected with a cover plate, and the cover plate extends downwards to form a second bulge corresponding to the size of the small end of the engine case; the positioning seat is also connected with a pressing plate, and the pressing plate is contacted with the outer side of the large end of the engine case; and the positioning seat is also provided with an anti-rotation hole, and the anti-rotation hole is connected with a positioning hole on the outer side of the large end of the engine case through a positioning pin.
2. A clip for an aircraft engine case according to claim 1, wherein: the engine casing positioning device further comprises an auxiliary supporting structure, the auxiliary supporting structure comprises a supporting part connected with the positioning seat, an inner supporting ring is connected onto the supporting part, and the top of the inner supporting ring is in contact with the bottom of an internal part of the engine casing.
3. A clip for an aircraft engine case according to claim 2, wherein: the lower end face of the inner support ring is provided with a connecting groove, and the support part extends into the connecting groove and is used for supporting the inner support ring.
4. A clip for an aircraft engine case according to claim 2, wherein: the inner support ring includes a shock absorbing layer at a top end.
5. A clip for an aircraft engine case according to claim 1, wherein: the pressing plate is Z-shaped.
6. A clip for an aircraft engine case according to claim 1, wherein: the top of the inner support column extends upwards to form a first positioning bulge, and a first positioning hole corresponding to the first positioning bulge is formed in the middle of the cover plate.
7. A clip for an aircraft engine case according to claim 6, wherein: the bottom of the inner support column extends downwards to form a second positioning bulge, and a second positioning hole corresponding to the second positioning bulge is formed in the middle of the positioning seat.
8. A clip for an aircraft engine case according to claim 1, wherein: the lower part of the inner support column is provided with a connecting part, and the connecting part is connected with the positioning seat through a connecting piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021231244.8U CN212552722U (en) | 2020-06-30 | 2020-06-30 | Clamp for aero-engine case |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021231244.8U CN212552722U (en) | 2020-06-30 | 2020-06-30 | Clamp for aero-engine case |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212552722U true CN212552722U (en) | 2021-02-19 |
Family
ID=74614175
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021231244.8U Active CN212552722U (en) | 2020-06-30 | 2020-06-30 | Clamp for aero-engine case |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212552722U (en) |
-
2020
- 2020-06-30 CN CN202021231244.8U patent/CN212552722U/en active Active
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