CN218639117U - Aeroengine dustcoat inner wall cutting process positioner - Google Patents
Aeroengine dustcoat inner wall cutting process positioner Download PDFInfo
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- CN218639117U CN218639117U CN202223161186.8U CN202223161186U CN218639117U CN 218639117 U CN218639117 U CN 218639117U CN 202223161186 U CN202223161186 U CN 202223161186U CN 218639117 U CN218639117 U CN 218639117U
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Abstract
The utility model provides an aeroengine dustcoat inner wall cutting process positioner, including the support, the support surface is equipped with the constant head tank, and the constant head tank internal face is the profiling face unanimous with aeroengine dustcoat surface shape, size, and the profiling face is attached to rubber and unloads the power pad. Adopt the technical scheme of the utility model, through with aeroengine dustcoat surface shape, the profile modeling of size unanimity is fixed a position and is supported in the face of the work piece, make the work piece pinpoint, thereby a foundation has been established for promoting work piece machining precision, and unload the power pad at profile modeling face adhesion rubber, rubber unloads the power pad and has the flexibility, on the one hand, can avoid causing the damage to the work piece surface when the clamping work piece, on the other hand, in the cutting process, the cutting force can unload the conduction effect of power pad through rubber, make cutting force evenly distributed treat the processing surface at the work piece, avoid the work piece local atress to appear and concentrate, prevent that local deformation from appearing in the work piece, the whole processingquality and whole outward appearance of work piece have been improved.
Description
Technical Field
The utility model belongs to the technical field of the cutting process equipment, especially, relate to an aeroengine dustcoat inner wall cutting positioning device.
Background
The outer cover of the aero-engine is a main appearance component in the aero-engine, the outer cover mainly plays a role of protecting other components in the aero-engine, the outer shape of the outer cover is generally in a thin-wall conical shell shape, and due to the fact that the wall thickness of the outer cover is extremely thin, a workpiece is very easy to deform due to the influence of cutting force in the process of machining and forming the outer cover of the aero-engine, and therefore a special positioning and clamping device is generally required to be manufactured for machining of the outer cover of the aero-engine.
For example, publication numbers are: the patent document of CN208992546U discloses a positioning fixture for machining an automobile engine housing, which comprises a supporting platform, wherein the supporting platform is provided with the positioning fixture, the positioning fixture consists of three groups of pressing mechanisms and three KOSMEK auxiliary supporting cylinders, each pressing mechanism consists of a lower bracket and a pressing component, each pressing component consists of a linear driving cylinder, a positioning column, a hinge support, a waist-shaped connecting block and a pressing block, the linear driving cylinder is arranged at the lower end of the supporting platform, the positioning column is arranged at the telescopic end of the linear driving cylinder, the lower end of the waist-shaped connecting block is hinged with the hinge support, the tail end of the pressing block is hinged with the upper end of the positioning column, the position, close to the head end, on the pressing block is hinged with the upper end of the waist-shaped connecting block, the patent technology is suitable for positioning the automobile engine housing to be machined, the rigidity of the automobile engine housing during machining can be increased, the deformation caused by the action of cutting force of a workpiece can be effectively reduced, and the machining precision and the machining quality are improved.
However, in the cutting process, the cutting force generated by the cutting tool on the workpiece is often concentrated on one point of the surface of the workpiece, and because most of the parts forming the process fixture are rigid metal members, the action range of the cutting force is too concentrated, so that the overall deformation of the workpiece is non-uniform, the local deformation of the workpiece is prominent, and the overall processing quality and the overall appearance of the workpiece are affected.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides an aeroengine dustcoat inner wall cutting process positioner.
The utility model discloses a following technical scheme can realize.
The utility model provides an aeroengine dustcoat inner wall cutting process positioner, which comprises a bracket, the support surface is equipped with the constant head tank, the constant head tank internal face is the profile face unanimous with aeroengine dustcoat surface shape, size, the profile face has attached to rubber and unloads the power pad.
The aero-engine outer cover inner wall cutting and positioning device further comprises a base, and the base is fixedly connected with the support through a fastening piece.
The surface of the base is also provided with a supporting boss, and the end face of the lower end of the bracket is consistent with the end face of the upper end of the supporting boss in shape and size.
The surface of the bracket is also provided with a space-avoiding sinking groove, and the fastening piece is arranged in the space-avoiding sinking groove.
The number of the fasteners is more than 4.
The positioning device for the cutting processing of the inner wall of the aircraft engine outer cover further comprises a positioning column, a screw and a compression nut, the lower end of the positioning column is fixedly connected with the support, the upper end of the positioning column is in threaded connection with the lower end of the screw, and the upper end of the screw is in threaded connection with the compression nut.
The support is integrally in the shape of an inverted cone frustum with a large upper end and a small lower end, the number of the positioning columns is multiple, and the plurality of the positioning columns are uniformly distributed around the central axis of the support in an array mode.
The positioning column is further in threaded connection with a back supporting screw, and the tail end of the back supporting screw abuts against the surface of the outer cover of the aircraft engine along the radial direction of the support.
The thread pitch of the back supporting screw is not more than 1.5mm.
The screw rod is sleeved with the gasket, and the gasket is arranged between the positioning column and the compression nut.
The beneficial effects of the utility model reside in that: adopt the technical scheme of the utility model, through with aeroengine dustcoat surface shape, the profile modeling of size unanimity is fixed a position and is supported in the face of the work piece, make the work piece pinpoint, thereby a foundation has been established for promoting work piece machining precision, and unload the power pad at profile modeling face adhesion rubber, rubber unloads the power pad and has the flexibility, on the one hand, can avoid causing the damage to the work piece surface when the clamping work piece, on the other hand, in the cutting process, the cutting force can unload the conduction effect of power pad through rubber, make cutting force evenly distributed treat the processing surface at the work piece, avoid the work piece local atress to appear and concentrate, prevent that local deformation from appearing in the work piece, the whole processingquality and whole outward appearance of work piece have been improved.
Drawings
FIG. 1 is a schematic view of the present invention;
FIG. 2 is an exploded view of the structure of the present invention;
FIG. 3 is a view of the present invention taken from the direction A of FIG. 2;
fig. 4 is a cross-sectional view taken along plane B-B of fig. 2 according to the present invention.
In the figure: 1-bracket, 2-aircraft engine housing, 3-base, 4-fastener, 5-positioning column, 6-screw, 7-gland nut, 8-counter screw, 9-gasket, 11-positioning groove, 12-rubber force-removing pad, 13-clearance sinking groove and 31-supporting boss.
Detailed Description
The technical solution of the present invention is further described below, but the scope of the claimed invention is not limited to the described.
As shown in fig. 1 to 4, the utility model provides an aeroengine dustcoat inner wall cutting positioning device, including support 1, support 1 surface is equipped with constant head tank 11, and constant head tank 11 internal face is the profile face unanimous with aeroengine dustcoat 2 surface shape, size, and profile face is attached to rubber and is unloaded power pad 12. Specifically, the rubber pad 12 is preferably made of rubber.
Adopt the technical scheme of the utility model, through with aeroengine dustcoat surface shape, the profile modeling of size unanimity is fixed a position and is supported in the face of the work piece, make the work piece pinpoint, thereby a foundation has been established for promoting work piece machining precision, and unload the power pad at profile modeling face adhesion rubber, rubber unloads the power pad and has the flexibility, on the one hand, can avoid causing the damage to the work piece surface when the clamping work piece, on the other hand, in the cutting process, the cutting force can unload the conduction effect of power pad through rubber, make cutting force evenly distributed treat the processing surface at the work piece, avoid the work piece local atress to appear and concentrate, prevent that local deformation from appearing in the work piece, the whole processingquality and whole outward appearance of work piece have been improved.
In addition, aeroengine dustcoat inner wall cutting process positioner still includes base 3, and base 3 links firmly together through using fastener 4 with support 1. The surface of the base 3 is also provided with a supporting boss 31, and the shape and the size of the end surface of the lower end of the bracket 1 are consistent with the shape and the size of the end surface of the upper end of the supporting boss 31. The surface of the bracket 1 is also provided with a space-avoiding sunk groove 13, and the fastening piece 4 is arranged in the space-avoiding sunk groove 13. The number of the fastening pieces 4 is 4 or more. The fastening piece 4 is preferably a hexagon socket head cap screw, so that the bracket 1 is supported through the base 3, the upper end surface and the lower end surface of the base 3 can be designed to be larger, and the flatness and the parallelism of the upper end surface and the lower end surface of the base 3 are improved by adopting a grinding method, so that the aeroengine housing workpiece is stably and reliably supported through the base 3 indirectly.
In addition, aeroengine dustcoat inner wall cutting process positioner still includes reference column 5, screw rod 6 and gland nut 7, and 5 lower extremes of reference column link firmly with support 1, and 5 upper ends of reference column and the 6 lower extreme spiro unions of screw rod, the 6 upper ends of screw rod and the 7 spiro unions of gland nut. And the edge of the aircraft engine outer cover 2 is clamped between the compression nut 7 and the upper end of the positioning column 5. Preferably, the support 1 is integrally in the shape of an inverted truncated cone with a large upper end and a small lower end, the number of the positioning columns 5 is multiple, and the plurality of positioning columns 5 are uniformly distributed around the central axis of the support 1 in an array manner. Therefore, the edge of the aeroengine outer cover workpiece is stably and reliably clamped, and a foundation is laid for improving the machining precision.
Specifically, the positioning column 5 is also screwed with a back support screw 8, and the end of the back support screw 8 radially abuts against the surface of the aircraft engine casing 2 along the support 1. Preferably, the thread pitch of the back-supporting screw 8 is not more than 1.5mm. The screw 6 is also sleeved with a washer 9, the washer 9 being arranged between the positioning post 5 and the compression nut 7. Therefore, acting force is applied to the workpiece through the back supporting screw 8, and the stress condition of the local area of the workpiece is finely adjusted.
Claims (10)
1. The utility model provides an aeroengine dustcoat inner wall cutting process positioner which characterized in that: the aircraft engine outer cover force-releasing device is characterized by comprising a support (1), wherein a positioning groove (11) is formed in the surface of the support (1), the inner wall surface of the positioning groove (11) is a profiling surface which is consistent with the surface shape and size of an aircraft engine outer cover (2), and a rubber force-releasing pad (12) is attached to the profiling surface.
2. The aircraft engine outer cover inner wall cutting positioning device according to claim 1, wherein: aeroengine dustcoat inner wall cutting process positioner still includes base (3), base (3) with support (1) links firmly together through using fastener (4).
3. The aircraft engine outer cover inner wall cutting positioning device according to claim 2, wherein: the surface of the base (3) is also provided with a supporting boss (31), and the shape and the size of the end surface of the lower end of the bracket (1) are consistent with those of the end surface of the upper end of the supporting boss (31).
4. The aircraft engine outer cover inner wall cutting positioning device according to claim 2, wherein: the surface of the support (1) is also provided with a space-avoiding sinking groove (13), and the fastening piece (4) is arranged in the space-avoiding sinking groove (13).
5. An aircraft engine housing inner wall cutting positioning device according to claim 4, characterized in that: the number of the fasteners (4) is more than 4.
6. An aircraft engine housing inner wall cutting positioning device according to any one of claims 1 to 4, characterized in that: aeroengine dustcoat inner wall cutting process positioner still includes reference column (5), screw rod (6) and gland nut (7), reference column (5) lower extreme with support (1) links firmly, reference column (5) upper end and screw rod (6) lower extreme spiro union, screw rod (6) upper end and gland nut (7) spiro union.
7. An aircraft engine shroud inner wall cutting positioning device as claimed in claim 6, wherein: the support (1) is integrally in the shape of an inverted truncated cone with a large upper end and a small lower end, the number of the positioning columns (5) is multiple, and the plurality of positioning columns (5) are uniformly distributed around the central axis of the support (1) in an array manner.
8. An aircraft engine shroud inner wall cutting positioning device as claimed in claim 7, wherein: the positioning column (5) is further in threaded connection with a back supporting screw (8), and the tail end of the back supporting screw (8) radially abuts against the surface of the aircraft engine outer cover (2) along the support (1).
9. The aero-engine housing inner wall cutting positioning device according to claim 8, wherein: the thread pitch of the back supporting screw (8) is not more than 1.5mm.
10. An aircraft engine shroud inner wall cutting positioning device as claimed in claim 6, wherein: the screw rod (6) is further sleeved with a gasket (9), and the gasket (9) is arranged between the positioning column (5) and the compression nut (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223161186.8U CN218639117U (en) | 2022-11-28 | 2022-11-28 | Aeroengine dustcoat inner wall cutting process positioner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223161186.8U CN218639117U (en) | 2022-11-28 | 2022-11-28 | Aeroengine dustcoat inner wall cutting process positioner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218639117U true CN218639117U (en) | 2023-03-17 |
Family
ID=85498637
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223161186.8U Active CN218639117U (en) | 2022-11-28 | 2022-11-28 | Aeroengine dustcoat inner wall cutting process positioner |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218639117U (en) |
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2022
- 2022-11-28 CN CN202223161186.8U patent/CN218639117U/en active Active
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