CN115519369A - Auxiliary supporting device for machining of aero-engine case - Google Patents
Auxiliary supporting device for machining of aero-engine case Download PDFInfo
- Publication number
- CN115519369A CN115519369A CN202211209716.3A CN202211209716A CN115519369A CN 115519369 A CN115519369 A CN 115519369A CN 202211209716 A CN202211209716 A CN 202211209716A CN 115519369 A CN115519369 A CN 115519369A
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- supporting
- casing
- plate
- base plate
- screw
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
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- Mechanical Engineering (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention discloses an auxiliary supporting device for cutting and machining of an aircraft engine casing, which comprises a transmission force measuring module and a clamp body, wherein the clamp body comprises a base plate and a pressing plate, and the pressing plate is used for clamping the end face of the casing on the base plate; the transmission force measuring module is circumferentially distributed on the top of the base plate and used for supporting the outer surface of the casing, the transmission force measuring module comprises a support frame, a pre-tightening device and a support unit, the support frame is fixed on the base plate, the pre-tightening device is fixed on the support frame, the support unit is used for clamping and supporting the outer surface of the casing, the support unit adjusts the support force through the pre-tightening device, and a force measuring sensor used for measuring the support force is arranged on the transmission force measuring module; according to the auxiliary supporting device for the cutting machining of the aero-engine case, the cutter relieving deformation phenomenon caused by turning force is reduced by improving the radial rigidity of the case, and the continuous adjustment of the pre-clamping force is realized by arranging the force measuring sensor and the pre-tightening device.
Description
Technical Field
The invention relates to the technical field of metal cutting machining, in particular to an auxiliary supporting device for the cutting machining of an aircraft engine casing.
Background
The problem of cutter relieving deformation faced by an aeroengine casing in the finish machining process has a great influence on the machining precision, the application of auxiliary support to a weak rigid structure of the casing is an important measure for improving the machining precision, and an auxiliary support tool not only needs to have good rigidity to share cutting force for the weak rigid part of the casing, but also needs to avoid the introduction of clamping deformation as much as possible, and simultaneously needs to consider the reliability, operability and the like of the tool.
The conventional auxiliary supporting tool for the thin-wall part is difficult to position and complicated in use, and consumes large time and labor cost in the dismounting process; easily generates clamping deformation; the tool is too heavy, the transportation and hoisting are difficult, and the loading of the machine tool is also a great challenge.
Disclosure of Invention
The invention aims to provide an auxiliary supporting device for machining of an aeroengine casing, which aims to solve the problems in the prior art, reduce the cutter relieving deformation caused by turning force by improving the radial rigidity of the casing, and realize continuous adjustment of pre-clamping force by arranging a force transducer and a pre-tightening device.
In order to achieve the purpose, the invention provides the following scheme:
the invention provides an auxiliary supporting device for cutting machining of an aircraft engine casing, which comprises a transmission force measuring module and a clamp body, wherein the clamp body comprises a base plate and a pressing plate, the pressing plate is circumferentially distributed on the top of the base plate, and the pressing plate is used for clamping the end face of the casing on the base plate; the transmission force measuring module is circumferentially distributed at the top of the base plate and used for supporting the outer surface of the casing, the transmission force measuring module comprises a support frame, a pre-tightening device and a support unit, the support frame is fixed on the base plate, the pre-tightening device is fixed on the support frame, the support unit is connected to the inner side of the pre-tightening device and used for clamping and supporting the outer surface of the casing, the support unit adjusts the supporting force through the pre-tightening device, and the transmission force measuring module is provided with a force measuring sensor used for measuring the supporting force.
Preferably, the pressing plate comprises a pressing part matched with the outline of the outer edge of the end face of the casing and a pre-tightening part connected with the substrate through screws, the pressing part is clamped on the end face of the casing, the two screws comprise a first screw and a second screw, and the pre-tightening part is connected with the substrate through the first screw and the second screw.
Preferably, the substrate is a circular plate structure, and the pressing plates are circumferentially and uniformly distributed on the substrate by taking the circle center of the substrate as the center.
Preferably, the transmission force measuring module is provided with 6.
Preferably, the periphery of the base plate is uniformly provided with 6 supporting plates in the circumferential direction, and the 6 supporting frames of the transmission force measuring modules are respectively installed at the tops of the supporting plates through bolts.
Preferably, the pre-tightening device comprises an outer shell, a guide sleeve, a push rod, a lead screw and a top plate, the outer shell is mounted on the support frame, a bottom cover is arranged at the outer end of the outer shell, the guide sleeve is mounted in the outer shell through a bolt, a guide hole is formed in the guide sleeve, one end of the push rod is connected in the guide hole in a sliding mode, the other end of the push rod is connected with the top plate, the top plate is connected with the support unit, a threaded hole is formed in the push rod, one end of the lead screw is connected in the threaded hole of the push rod in a threaded mode, and the other end of the lead screw penetrates through the guide sleeve and the bottom cover to extend out of the outer shell; the screw rod is rotated to enable the ejector rod to move inside and outside along the guide hole of the guide sleeve.
Preferably, a balance plate is installed between the bottom cover and the guide sleeve, the balance plate is clamped outside the screw rod, and the balance plate is used for supporting the screw rod and realizing axial limiting of the screw rod.
Preferably, the load cell is disposed between the bottom cover and the balance plate.
Preferably, two pretensioning devices with the supporting units are arranged on each supporting frame along the vertical direction.
Preferably, the supporting unit is an arc-shaped plate matched with the outer profile of the casing.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides an auxiliary supporting device for machining of an aircraft engine casing, which comprises two modules, namely a clamp body and a transmission force measuring module, wherein the clamp body is a carrier for connecting all components of the whole clamp and plays a role in connecting and integrally supporting and positioning the tool. The transmission force measuring module is circumferentially arranged on the fixture body around the casing, all supporting releasing functions and all clamping force measuring functions are integrated on the transmission force measuring module, the transmission force measuring module can synchronously measure the clamping force while clamping the outer surface of the casing, the cutter relieving deformation phenomenon caused by turning force is reduced by improving the radial rigidity of the casing, the influence of the pre-clamping force on the supporting rigidity of the external supporting tool is considered, a force measuring sensor and a pre-tightening device are introduced in the design of the tool by considering the quantitative clamping problem, and the continuous adjustment of the pre-clamping force is realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic perspective view of an auxiliary supporting device for machining an aircraft engine casing according to the present invention;
FIG. 2 is a schematic view of a transmission force measuring module according to the present invention;
FIG. 3 is a schematic top view of the clamp body of the present invention;
FIG. 4 isbase:Sub>A sectional view taken along line A-A of FIG. 3;
in the figure: 1-transmission force measuring module, 101-support frame, 102-pre-tightening device, 103-support unit, 104-outer shell, 105-guide sleeve, 106-top rod, 107-screw rod, 108-force measuring sensor, 109-top plate, 110-bolt, 111-bottom cover and 112-balance plate;
2-clamp body, 201-base plate, 202-pressure plate, 203-screw I, 204-screw II and 206-support plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide an auxiliary supporting device for machining of an aeroengine casing, which aims to solve the problems in the prior art.
In order to make the aforementioned objects, features and advantages of the present invention more comprehensible, the present invention is described in detail with reference to the accompanying drawings and the detailed description thereof.
As shown in fig. 1-4, the auxiliary supporting device for machining an aircraft engine casing in the embodiment includes a transmission force measuring module 1 and a clamp body 2, where the clamp body 2 includes a base plate 201 and a pressing plate 202, the pressing plate 202 is circumferentially distributed on the top of the base plate 201, and the pressing plate 202 is used for clamping an end face of the casing on the base plate 201; the transmission force measuring module 1 is circumferentially distributed on the top of the base plate 201 and used for supporting the outer surface of the casing, the transmission force measuring module 1 comprises a supporting frame 101, a pre-tightening device 102 and a supporting unit 103, the supporting frame 101 is fixed on the base plate 201, the pre-tightening device 102 is fixed on the supporting frame 101, the supporting unit 103 is connected to the inner side of the pre-tightening device 102, the supporting unit 103 is used for clamping and supporting the outer surface of the casing, the supporting unit 103 adjusts supporting force through the pre-tightening device 102, and a force measuring sensor 108 used for measuring the supporting force is arranged on the transmission force measuring module 1.
In this embodiment, the pressing plate 202 includes a pressing portion adapted to the contour of the outer edge of the casing end surface and a pre-tightening portion connected to the substrate 201 through a screw, the pressing portion is clamped to the casing end surface, the screw includes two screws, i.e., a first screw 203 and a second screw 204, the pre-tightening portion is connected to the substrate 201 through the first screw 203 and the second screw 204, and the pressing plate 202 can be pressed to the casing end surface by adjusting the first screw 203 and the second screw 204.
In the present embodiment, the substrate 201 is a circular plate structure, and the pressing plates 202 are circumferentially and uniformly distributed on the substrate 201 around the center of the circle of the substrate 201.
In this embodiment, there are 6 transmission force-measuring modules 1, 6 support plates 206 are uniformly distributed on the periphery of the base plate 201, and the support frames 101 of the 6 transmission force-measuring modules 1 are respectively mounted on the top of the support plates 206 through bolts 110.
In this embodiment, the pre-tightening device 102 includes an outer housing 104, a guide sleeve 105, a top rod 106, a lead screw 107 and a top plate 109, the outer housing 104 is mounted on the support frame 101, a bottom cover 111 is disposed at an outer end of the outer housing 104, the guide sleeve 105 is mounted in the outer housing 104 through a bolt 110, a guide hole is disposed inside the guide sleeve 105, one end of the top rod 106 is slidably connected in the guide hole, the other end of the top rod 106 is connected to the top plate 109, the top plate 109 is connected to the support unit 103, a threaded hole is disposed inside the top rod 106, one end of the lead screw 107 is threadedly connected in the threaded hole of the top rod 106, and the other end of the lead screw 107 penetrates through the guide sleeve 105 and the bottom cover 111 and extends out of the outer housing 104; the rotation of the screw 107 can move the rod 106 along the guide hole of the guide sleeve 105, so that the top plate 109 with the support unit 103 provides a holding support force for the casing.
In this embodiment, a balance plate 112 is installed between the bottom cover 111 and the guide sleeve 105, the balance plate 112 is clamped outside the screw 107, and the balance plate 112 is used for supporting the screw 107 and realizing axial limiting of the screw 107. The load cell 108 is disposed between the bottom cover 111 and the balance plate 112, and the load cell 108 measures the magnitude of the supporting force.
In this embodiment, two pre-tightening devices 102 with supporting units 103 are disposed on each supporting frame 101 along the vertical direction, and the two pre-tightening devices 102 individually control the corresponding supporting units 103.
In this embodiment, the supporting unit 103 is an arc plate matching with the outer profile of the casing.
The auxiliary supporting device for the cutting machining of the aero-engine case provided by the invention comprises the following operation steps:
the method comprises the following steps: the auxiliary supporting device is arranged and installed according to the figure 1, six groups of transmission force measuring modules 1 which are uniformly distributed in an annular mode are used for supporting the outer surface of the casing, a group of clamp bodies 2 are used for clamping the end face of the casing, and a base plate 201, a pressing plate 202, a first screw 203 and a second screw 204 are used for achieving pressing.
Step two: the support unit 103 is attached to the outer surface of the casing by rotating a screw 107 in the transmission force-measuring module 1, and initial pre-clamping force is obtained by a force sensor.
Step three: and finishing the cutting of the inner surface of the casing under the condition of auxiliary support, and measuring the cutter back-off deformation condition of the part.
Step four: the pre-clamping force of the supporting unit 103 is adjusted by rotating the screw rod 107, and the corresponding supporting force is measured by the force sensor, so that the deformation tendency of the inner surface of the casing after cutting is reduced, and the high-quality processing of parts is realized.
The principle and the implementation mode of the invention are explained by applying specific examples, and the description of the above examples is only used for helping understanding the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In summary, this summary should not be construed to limit the present invention.
Claims (10)
1. The utility model provides an aeroengine machine casket cutting process auxiliary stay device which characterized in that: the clamp comprises a transmission force measuring module and a clamp body, wherein the clamp body comprises a base plate and a pressing plate, the pressing plate is circumferentially distributed on the top of the base plate, and the pressing plate is used for clamping the end face of a casing on the base plate; the transmission force measuring module is circumferentially distributed at the top of the base plate and used for supporting the outer surface of the casing, the transmission force measuring module comprises a support frame, a pre-tightening device and a support unit, the support frame is fixed on the base plate, the pre-tightening device is fixed on the support frame, the support unit is connected to the inner side of the pre-tightening device and used for clamping and supporting the outer surface of the casing, the support unit adjusts the supporting force through the pre-tightening device, and the transmission force measuring module is provided with a force measuring sensor used for measuring the supporting force.
2. The aero-engine case cutting auxiliary support device according to claim 1, wherein: the pressing plate comprises a pressing part and a pre-tightening part, the pressing part is matched with the outline of the outer edge of the end face of the casing, the pre-tightening part is connected with the substrate through a screw, the pressing part is clamped on the end face of the casing, the screw is provided with two screws including a screw I and a screw II, and the pre-tightening part is connected with the substrate through the screw I and the screw II.
3. The aero-engine case cutting auxiliary support device according to claim 1, wherein: the base plate is of a circular plate body structure, and the pressing plates are circumferentially and uniformly distributed on the base plate by taking the circle center of the base plate as the center.
4. The aero-engine case cutting auxiliary support device according to claim 1, wherein: the number of the transmission force measuring modules is 6.
5. The aero-engine case cutting auxiliary support device according to claim 4, wherein: the periphery circumference equipartition of base plate has 6 backup pads, and 6 the support frame of transmission dynamometry module is respectively through the bolt mounting in the top of backup pad.
6. The aero-engine case cutting auxiliary support device according to claim 5, wherein: the pre-tightening device comprises an outer shell, a guide sleeve, a push rod, a lead screw and a top plate, wherein the outer shell is arranged on the support frame, a bottom cover is arranged at the outer end of the outer shell, the guide sleeve is arranged in the outer shell through a bolt, a guide hole is formed in the guide sleeve, one end of the push rod is connected in the guide hole in a sliding mode, the other end of the push rod is connected with the top plate, the top plate is connected with the supporting unit, a threaded hole is formed in the push rod, one end of the lead screw is connected in the threaded hole of the push rod in a threaded mode, and the other end of the lead screw penetrates through the guide sleeve and the bottom cover to extend out of the outer shell; the screw rod is rotated to enable the ejector rod to move inside and outside along the guide hole of the guide sleeve.
7. The aero-engine case cutting auxiliary support device according to claim 6, wherein: the bottom with install the balance plate between the guide sleeve, the balance plate connect in the outside of lead screw, the balance plate is used for supporting when the lead screw, realize the axial of lead screw is spacing.
8. The aero-engine case cutting auxiliary support device according to claim 7, wherein: the load cell is arranged between the bottom cover and the balance plate.
9. The aero-engine case cutting auxiliary support device according to claim 1, wherein: two pre-tightening devices with the supporting units are arranged on each supporting frame along the vertical direction.
10. The aero-engine case cutting auxiliary support device according to claim 1, wherein: the supporting unit is an arc-shaped plate matched with the outline of the outer surface of the casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211209716.3A CN115519369A (en) | 2022-09-30 | 2022-09-30 | Auxiliary supporting device for machining of aero-engine case |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211209716.3A CN115519369A (en) | 2022-09-30 | 2022-09-30 | Auxiliary supporting device for machining of aero-engine case |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115519369A true CN115519369A (en) | 2022-12-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211209716.3A Pending CN115519369A (en) | 2022-09-30 | 2022-09-30 | Auxiliary supporting device for machining of aero-engine case |
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| CN (1) | CN115519369A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116441924A (en) * | 2023-06-19 | 2023-07-18 | 四川顶锐液压设备制造有限公司 | Assembling system and assembling method for aero-engine unit body |
-
2022
- 2022-09-30 CN CN202211209716.3A patent/CN115519369A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116441924A (en) * | 2023-06-19 | 2023-07-18 | 四川顶锐液压设备制造有限公司 | Assembling system and assembling method for aero-engine unit body |
| CN116441924B (en) * | 2023-06-19 | 2023-08-22 | 四川顶锐液压设备制造有限公司 | Assembling system and assembling method for aero-engine unit body |
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