CN116460631A - Flexible clamping system for aero-engine blade part - Google Patents
Flexible clamping system for aero-engine blade part Download PDFInfo
- Publication number
- CN116460631A CN116460631A CN202310376181.7A CN202310376181A CN116460631A CN 116460631 A CN116460631 A CN 116460631A CN 202310376181 A CN202310376181 A CN 202310376181A CN 116460631 A CN116460631 A CN 116460631A
- Authority
- CN
- China
- Prior art keywords
- clamping
- blade part
- clamping device
- mounting hole
- movable
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000010720 hydraulic oil Substances 0.000 claims description 45
- 239000003921 oil Substances 0.000 claims description 37
- 239000007788 liquid Substances 0.000 claims description 5
- 239000000523 sample Substances 0.000 claims description 4
- 238000003754 machining Methods 0.000 abstract description 9
- 238000007493 shaping process Methods 0.000 description 10
- 238000000034 method Methods 0.000 description 7
- 230000001788 irregular Effects 0.000 description 4
- 238000003801 milling Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
Classifications
-
- 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
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/08—Work-clamping means other than mechanically-actuated
-
- 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
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
- B23Q3/08—Work-clamping means other than mechanically-actuated
- B23Q3/082—Work-clamping means other than mechanically-actuated hydraulically actuated
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The application discloses aeroengine blade part clamping system relates to the technical field of blade part processing. The clamping system for the aero-engine blade part comprises a workbench, wherein a first clamping device and a second clamping device are sequentially arranged on the workbench; the second clamping device comprises two clamping blocks capable of moving oppositely and away from each other, a plurality of mounting holes are formed in the clamping surface of each clamping block, movable pieces are slidably arranged in each mounting hole, a plurality of movable pieces on one clamping block are abutted against a plurality of movable pieces on the other clamping block, and each movable piece can be reset after sliding; and an elastic piece for pressing the movable piece is further arranged in each mounting hole. The blade part clamping device can clamp the blade part stably, so that the machining precision of the blade part is guaranteed.
Description
Technical Field
The application relates to the technical field of blade part machining, in particular to an aero-engine blade part clamping system.
Background
At present, a plurality of blade parts are usually machined and then assembled, and a five-axis milling mode is usually used for machining single blade parts. When milling, clamping and positioning are needed to be carried out on any one end of a blank of a single blade part, the blank of the single blade part is centered, then the other end of the blank of the blade part which is not clamped can be machined and molded, then the blank of the blade part is turned over to clamp one end which is machined and molded, and then the whole blade part can be machined and molded, wherein the blade part is of an irregular structure after being molded, when the blank of the blade part is turned over to clamp one end which is molded on the blank of the blade part, the stable clamping of the blade part is difficult to ensure, and then the centering of the clamped blank of the blade part after being turned over is difficult to be accurate, so that the follow-up machining precision cannot be ensured.
Disclosure of Invention
In order to enable the blade part to be stably clamped as much as possible, and therefore machining precision of the blade part is guaranteed, the application provides an aero-engine blade part clamping system.
The application provides an aeroengine blade part clamping system adopts following technical scheme:
the clamping system for the blade part of the aeroengine comprises a workbench, wherein a first clamping device and a second clamping device are sequentially arranged on the workbench, the first clamping device is used for clamping a blank end of the blade part, and the second clamping device is used for clamping a forming end of the blade part;
the second clamping device comprises two clamping blocks capable of moving oppositely and away from each other, a plurality of mounting holes are formed in the clamping surface of each clamping block, movable pieces are slidably arranged in each mounting hole, a plurality of movable pieces on one clamping block are abutted against a plurality of movable pieces on the other clamping block, and each movable piece can be reset after being slidably moved; and an elastic piece for pressing the movable piece is further arranged in each mounting hole.
Through adopting above-mentioned technical scheme, first clamping device of drive at first is with the one end centre gripping of blade part blank, then carries out processing and shaping with the other end of blade part blank, later drives second clamping device and carries out the centre gripping with blade part shaping end, then drives first clamping device and unclamps the blank end of blade part, can process the remaining blank end of blade part this moment, does not change in the position of blade part in the whole process flow of blade part blank, and this design can guarantee the machining precision of blade part to a certain extent. The second clamping device clamps the forming end of the blade part: firstly, the movable pieces on different clamping blocks are guaranteed to be separated, then the forming end of the blade part is guaranteed to be positioned between the two clamping blocks, then the two clamping blocks are close to each other, the two clamping blocks drive a plurality of movable pieces to move towards the forming end of the blade part, the movable pieces can be enabled to support and press the blade part in a self-adapting mode, and finally after the two clamping blocks are close to each other and reset, the movable pieces are pressed to fix the movable pieces by utilizing the elastic pieces, so that the movable pieces can clamp the forming end of the blade part stably.
Preferably, each elastic piece is arranged on the inner wall of the mounting hole, a hydraulic oil cavity is formed between each elastic piece and the inner wall of the mounting hole, and each hydraulic oil cavity is used for taking oil so that the elastic piece deforms to compress the movable piece; each clamping block is provided with a liquid oil channel communicated with each hydraulic oil cavity, and each liquid oil channel is provided with an oil inlet.
Through adopting above-mentioned technical scheme, after injecting hydraulic oil to the oil inlet in, hydraulic oil can reach each hydraulic oil pocket through the liquid oil passageway, thereby the continuous oil feed in the hydraulic oil pocket can make elastic component deformation compress tightly the moving part.
Preferably, an oil inlet control bolt is arranged on the oil inlet through threads, the oil inlet is sealed by the oil inlet control bolt, and the oil inlet control bolt is used for controlling oiling in the hydraulic oil cavity.
By adopting the technical scheme, firstly, hydraulic oil needs to be injected into the hydraulic oil channel in advance, and the hydraulic oil needs to be ensured to fill the hydraulic oil channel and each hydraulic oil cavity, and at the moment, the hydraulic oil in the hydraulic oil cavity can be extruded by screwing the oil inlet control bolt, so that the elastic piece can be deformed; after the oil inlet control bolt is reversely screwed and reset, hydraulic oil is reset due to the reset of the elastic piece.
Preferably, each mounting hole is a blind hole, a spring is arranged between the mounting hole and the movable piece, one end of the spring is arranged on the bottom surface of the mounting hole, and the other end of the spring is arranged on the movable piece.
By adopting the technical scheme, in the process of clamping the forming end of the blade part, the spring is used for ensuring that the movable part fully presses the forming end of the blade part; when the two clamping blocks are separated to release the clamping of the forming end of the blade part, the movable part can be reset under the action of the spring; the spring can also prevent the movable member from being disengaged from the mounting hole.
Preferably, the mounting hole is internally provided with a propping part, the movable piece is provided with a protruding part, the protruding part is positioned between the propping part and the inner bottom surface of the mounting hole, and the propping part is used for propping against the protruding part so that the movable range of the movable piece is limited.
By adopting the technical scheme, the abutting part and the protruding part can further ensure that the movable part cannot be separated from the mounting hole, and the limitation of the movable range of the movable part can ensure that the spring cannot be damaged due to excessive deformation.
Preferably, each movable part is a probe, and the abutting surface of each movable part is an arc surface.
Through adopting above-mentioned technical scheme, a plurality of probes can be densely covered and contradicted on the shaping end of blade part, and the arcwall face can protect the structure of blade part shaping end.
Preferably, a plurality of contact points are formed by propping a plurality of movable pieces on one clamping block and a plurality of movable pieces on the other clamping block, and the plurality of contact points are positioned in the same vertical plane.
Through adopting above-mentioned technical scheme, after a plurality of moving parts contradict the blade part, this design can make the blade part receive comparatively even from the power of a plurality of moving parts.
Preferably, the first clamping device is provided with a first positioning block and a second positioning block, the first positioning block is used for positioning the blade part in the vertical direction, the second positioning block is provided with a positioning notch, and the positioning notch is used for positioning the blade part in the transverse direction.
Through adopting above-mentioned technical scheme, before the one end of drive first clamping device with the blade part carries out the centre gripping, can place the blade part on first positioning block and guarantee that the blade part also is located the location breach, first positioning block can fix a position the blade part in vertical direction, and the location breach can make the blade part fix a position in horizontal direction.
Preferably, a sliding groove is formed in the bottom of the first clamping device, a wire rail is arranged on the workbench and clamped in the sliding groove, and the first clamping device can reciprocate towards the second clamping device.
By adopting the technical scheme, the first clamping device can be moved in the direction away from the second clamping device, so that the upper blade part blank can be clamped on the first clamping device conveniently; after one end of the blade part is molded, the first clamping device can be moved to drive the blade part to move, so that the clamped position of the molded section of the blade part is adjusted, and the molded section of the blade part is ensured to be stably clamped.
Preferably, the clamping area on the first clamping device is a first clamping area, the clamping area on the second clamping device is a second clamping area, and the first clamping area and the second clamping area are adjacent in the transverse direction.
Through adopting above-mentioned technical scheme, can guarantee when first clamping device is to the one end centre gripping of blade part, the second clamping device also can carry out the centre gripping with the other end of blade part simultaneously, and this design aims at guaranteeing that the blade part can not appear the position deflection when being passed by the second clamping device in from being held by first clamping device.
In summary, the present invention includes at least one of the following beneficial technical effects:
1. the following processing flow can be realized: the blade part blank is characterized in that the blade part blank is provided with a first clamping device, one end of the blade part blank is clamped by the first clamping device, the other end of the blade part blank is machined and molded, the molded end of the blade part is clamped by a second clamping device, the blank end of the blade part is loosened by the first clamping device, the rest blank end of the blade part can be machined at the moment, the position of the blade part is unchanged in the whole machining process of the blade part blank, and the machining precision of the blade part can be guaranteed to a certain extent by the design. The second clamping device clamps the forming end of the blade part: firstly, ensuring that movable pieces on different clamping blocks are separated, then ensuring that the forming end of a blade part is positioned between two clamping blocks, then enabling the two clamping blocks to be close to each other, enabling the two clamping blocks to drive a plurality of movable pieces to move towards the forming end of the blade part so that the plurality of movable pieces can adaptively press the blade part, and finally after the two clamping blocks are close to each other and reset, compressing the movable pieces to fix the movable pieces by using elastic pieces, so that the plurality of movable pieces can clamp the forming end of the blade part stably;
2. firstly, hydraulic oil needs to be injected into a hydraulic oil channel in advance, and the hydraulic oil needs to be ensured to fill the hydraulic oil channel and each hydraulic oil cavity, and at the moment, the hydraulic oil in the hydraulic oil cavity can be extruded by screwing an oil inlet control bolt, so that the elastic piece can be deformed; after the oil inlet control bolt is reversely screwed and reset, hydraulic oil is reset due to the reset of the elastic piece.
Drawings
FIG. 1 is a schematic view of the overall structure of an aircraft engine blade member clamping system clamping a blade member blank in an embodiment of the present application;
FIG. 2 is a schematic view of a first clamping device clamping a blank end of a bucket component;
FIG. 3 is a cross-sectional view of a second clamping device clamping a profiled end of a blade member;
fig. 4 is an enlarged view of a portion a in fig. 3.
The reference numerals in the drawings: 1. a work table; 11. a wire rail; 2. a first clamping device; 21. a first clamping area; 22. a first positioning block; 23. a second positioning block; 231. positioning the notch; 3. a second clamping device; 31. a second clamping area; 32. a clamping block; 321. a mounting hole; 322. a movable member; 3221. a boss; 3222. a contact point; 3223. an arc surface; 323. an elastic member; 3231. a hydraulic oil chamber; 3232. an oil feed control bolt; 324. a spring; 325. and a butting part.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
In the description of the present invention, it should be understood that references to orientation descriptions such as upper, lower, front, rear, left, right, etc. are based on the orientation or positional relationship shown in the drawings, are merely for convenience of description of the present invention and to simplify the description, and do not indicate or imply that the apparatus or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the present invention.
The embodiment of the application discloses an aeroengine blade part clamping system. The clamping device is used for stably clamping the blade part with the irregular structure, so that the milling precision of a finished product of the blade part is ensured. Referring to fig. 1, an aeroengine blade component clamping system includes a workbench 1, a first clamping device 2 and a second clamping device 3 are sequentially arranged on the workbench 1 from left to right, the first clamping device 2 can clamp a blank end of a blade component, namely a regular structure, the second clamping device 3 can clamp a forming end of the blade component, namely an irregular structure, a sliding groove is formed in the bottom of the first clamping device 2, a wire rail 11 is arranged on the workbench 1, the wire rail 11 is clamped in the sliding groove, the arrangement direction of the wire rail 11 is set to be an x axis, a direction which is transverse to the x axis and perpendicular to the x axis is set to be a y axis, a direction which is vertical to the x axis and perpendicular to the x axis is set to be a z axis, the first clamping device 2 can reciprocate on the workbench 1 along the x axis direction, and the first clamping device 2 and the second clamping device 3 are self-centering vices. The clamping area on the first clamping device 2 is a first clamping area 21, the clamping area on the second clamping device 3 is a second clamping area 31, the center of the first clamping area 21 and the center of the second clamping area 31 are located on the same straight line arranged along the x-axis direction, the first clamping area 21 and the second clamping area 31 are adjacent in the transverse direction, and the design can ensure that the first clamping device 2 and the second clamping device 3 can clamp the blade part simultaneously.
Referring to fig. 2, in order to enable the blade part blank to be clamped by the first clamping device 2 relatively accurately, the first clamping device 2 is further provided with a first positioning block 22 and a second positioning block 23, and in combination with fig. 1, the first positioning block 22 is located below the first clamping area 21, the second positioning block 23 is located on the right side of the first clamping area 21, the first positioning block 22 is used for supporting the blade part, so that the blade part is positioned in the z-axis direction, the second positioning block 23 is provided with a positioning notch 231, the blade part can be arranged in the positioning notch 231 in a penetrating manner, and the positioning notch 231 is used for positioning the blade part in the y-axis direction.
The processing process of the blade part is as follows: first clamping device 2 is moved along the direction that x axial is far away from second clamping device 3, then place the blade part on first locating piece 22, and guarantee that first locating piece 22 wears to establish in location breach 231, drive first clamping device 2 this moment and hold one end of blade part blank, then carry out processing and shaping with the other end of blade part blank, afterwards move first clamping device 2 along the direction that x axial is close to second clamping device 3 with the blade part until the shaping end of blade part gets into second clamping area 31, afterwards drive second clamping device 3 carries out the centre gripping with the blade part shaping end, afterwards drive first clamping device 2 loosens the blank end of blade part, can process the processing with the blank end that the blade part remains in order to accomplish the processing of whole blade part this moment. The position of the blade part can be easily measured and calculated in the whole processing flow of the blade part blank, namely, the blade part does not have position deflection, and the design can ensure the milling processing precision of the blade part to a certain extent.
Referring to fig. 3, a specific structure for implementing the second clamping device 3 to clamp the irregular structure in the embodiment of the present application is: the second clamping device 3 comprises two clamping blocks 32 capable of moving in opposite directions or in opposite directions along the y-axis direction, and referring to fig. 4, a mounting hole 321 is formed in a clamping surface of each clamping block 32, and a plurality of mounting holes 321 are uniformly distributed on the clamping blocks 32. All slide in each mounting hole 321 and be equipped with movable part 322, movable part 322 can be along y axle direction motion, and movable part 322 can reset after sliding, still is equipped with the elastic component 323 that is used for compressing tightly movable part 322 in each mounting hole 321, and elastic component 323 is the oil pressure tight cover that expands in this application embodiment.
The clamping process of the second clamping device 3 for clamping the forming end of the blade part is as follows: firstly, the movable pieces 322 on different clamping blocks 32 are ensured to be separated, the forming ends of the blade parts are ensured to be positioned in the second clamping area 31, then the second clamping device 3 is driven to enable the two clamping blocks 32 to move towards each other, any one clamping block 32 drives a plurality of movable pieces 322 to move towards the forming ends of the blade parts, so that the plurality of movable pieces 322 can adaptively press the blade parts, and finally after the two clamping blocks 32 are mutually close to reset, the movable pieces 322 can be pressed by the elastic pieces 323 to fix the movable pieces 322, so that the second clamping device 3 clamps the forming ends of the blade parts.
Referring to fig. 3 and 4, some specific structures in the mounting hole 321 in the embodiment of the present application are: the mounting hole 321 is the blind hole, all be equipped with spring 324 between mounting hole 321 and the movable part 322, on the bottom surface of mounting hole 321 was located to the one end of spring 324, on the movable part 322 was located to the other end of spring 324, spring 324 can inject the movable range of movable part 322, in carrying out the centre gripping to the blade part shaping end, spring 324 can make movable part 322 fully support the pressure to the blade part shaping end, when two clamp pieces 32 are separated and release the centre gripping to the shaping end of blade part, movable part 322 can reset because the effect of spring 324. The mounting hole 321 is provided with a propping portion 325, the movable piece 322 is provided with a protruding portion 3221, the protruding portion 3221 is located between the propping portion 325 and the inner bottom surface of the mounting hole 321, and the propping portion 325 is used for propping against the protruding portion 3221 so as to further limit the movable range of the movable piece 322.
Referring to fig. 3, some specific structures of the movable member 322 in this embodiment are: a plurality of abutting points 3222 are formed on a plurality of moving parts 322 on one clamping block 32 and a plurality of moving parts 322 on the other clamping block 32 in an abutting mode, the abutting points 3222 are located in the same vertical plane, each moving part 322 is a probe, the abutting surface of each moving part 322 is an arc-shaped surface 3223, and the arc-shaped surface 3223 can enable the structure of a forming end of the blade part to be protected when the moving parts 322 abut on the blade part.
Referring to fig. 4, some specific structures for implementing the compression of the movable member 322 by the elastic member 323 in the embodiment of the present application are: each elastic piece 323 is arranged on the inner wall of the mounting hole 321 and can deform to press the movable piece 322 positioned in the same mounting hole 321, a hydraulic oil cavity 3231 is formed between each elastic piece 323 and the inner wall of the mounting hole 321, and each hydraulic oil cavity 3231 is used for feeding oil so that the elastic piece 323 deforms to press the movable piece 322. Referring to fig. 3, each clamping block 32 is provided with a hydraulic oil passage connected to each hydraulic oil chamber 3231, and each hydraulic oil passage is provided with an oil inlet formed in the clamping block 32. An oil inlet control bolt 3232 is arranged on the oil inlet through threads, the oil inlet is closed by the oil inlet control bolt 3232, and the oil inlet control bolt 3232 is used for controlling oiling in the hydraulic oil cavity 3231.
Firstly, hydraulic oil needs to be injected into a hydraulic oil channel in advance, and the hydraulic oil needs to be ensured to fill the hydraulic oil channel and each hydraulic oil cavity 3231, at the moment, the hydraulic oil in the hydraulic oil cavity 3231 can be extruded by screwing the oil inlet control bolt 3232, so that the elastic piece 323 can be deformed, and then the movable piece 322 is compressed by the elastic piece 323; after the oil feed control bolt 3232 is reversely screwed and reset, hydraulic oil is reset due to the reset of the elastic member 323.
The implementation principle of the clamping system for the blade part of the aero-engine in the embodiment of the application is as follows: firstly, moving the first clamping device 2 along the x-axis direction away from the second clamping device 3, then placing the blade part on the first positioning block 22, ensuring that the first positioning block 22 is arranged in the positioning notch 231 in a penetrating way, driving the first clamping device 2 to clamp one end of the blade part blank, and then machining and forming the other end of the blade part blank;
firstly, the movable pieces 322 on different clamping blocks 32 are required to be separated, then the first clamping device 2 is moved along the direction that the x axis approaches the second clamping device 3 along the blade component until the forming end of the blade component enters the second clamping area 31, then the second clamping device 3 is driven to enable the two clamping blocks 32 to move towards each other, in the moving process of the clamping blocks 32, a plurality of movable pieces 322 can be adaptively pressed against the blade component, after the two clamping blocks 32 are mutually close to reset, the oil inlet control bolts 3232 are screwed to enable hydraulic oil in the hydraulic oil cavity 3231 to squeeze the elastic pieces 323, so that the elastic pieces 323 are deformed, the movable pieces 322 are compressed by deformation of the elastic pieces 323, at the moment, the blade component is clamped by the second clamping device 3, then the first clamping device 2 is driven to loosen the blank end of the blade component, at the moment, the rest blank end of the blade component can be processed to finish the processing of the whole blade component.
The embodiments of the present invention are all preferred embodiments of the present invention, and are not intended to limit the scope of the present invention in this way, therefore: all equivalent changes in structure, shape and principle of the invention should be covered in the scope of protection of the invention.
Claims (10)
1. An aero-engine blade component clamping system, characterized by: the novel blade forming machine comprises a workbench (1), wherein a first clamping device (2) and a second clamping device (3) are sequentially arranged on the workbench (1), the first clamping device (2) is used for clamping a blank end of a blade part, and the second clamping device (3) is used for clamping a forming end of the blade part;
the second clamping device (3) comprises two clamping blocks (32) capable of moving oppositely and away from each other, a plurality of mounting holes (321) are formed in the clamping surface of each clamping block (32), movable pieces (322) are slidably arranged in each mounting hole (321), the movable pieces (322) on one clamping block (32) are in contact with the movable pieces (322) on the other clamping block (32), and each movable piece (322) can slide and then reset; and an elastic piece (323) used for pressing the movable piece (322) is further arranged in each mounting hole (321).
2. An aircraft engine blade part clamping system according to claim 1, wherein: each elastic piece (323) is arranged on the inner wall of the mounting hole (321), a hydraulic oil cavity (3231) is formed between each elastic piece (323) and the inner wall of the mounting hole (321), and each hydraulic oil cavity (3231) is used for feeding oil so that the elastic piece (323) deforms to compress the movable piece (322); each clamping block (32) is provided with a liquid oil channel communicated with each hydraulic oil cavity (3231), and each liquid oil channel is provided with an oil inlet on the clamping block (32).
3. An aircraft engine blade part clamping system according to claim 2, wherein: an oil inlet control bolt (3232) is arranged on the oil inlet through threads, the oil inlet is sealed by the oil inlet control bolt (3232), and the oil inlet control bolt (3232) is used for controlling oiling in the hydraulic oil cavity (3231).
4. An aircraft engine blade part clamping system according to claim 1, wherein: each mounting hole (321) is a blind hole, a spring (324) is arranged between each mounting hole (321) and each movable piece (322), one end of each spring (324) is arranged on the bottom surface of each mounting hole (321), and the other end of each spring (324) is arranged on each movable piece (322).
5. An aircraft engine blade part clamping system according to claim 4, wherein: the mounting hole (321) is internally provided with a propping part (325), the movable piece (322) is provided with a protruding part (3221), the protruding part (3221) is positioned between the propping part (325) and the inner bottom surface of the mounting hole (321), and the propping part (325) is used for propping against the protruding part (3221) so that the movable range of the movable piece (322) is limited.
6. An aircraft engine blade part clamping system according to claim 1, wherein: each movable piece (322) is a probe, and the abutting surface of each movable piece (322) is an arc-shaped surface (3223).
7. An aircraft engine blade part clamping system according to claim 6, wherein: a plurality of contact points (3222) are formed by abutting a plurality of movable pieces (322) on one clamping block (32) and a plurality of movable pieces (322) on the other clamping block (32), and a plurality of contact points (3222) are positioned in the same vertical plane.
8. An aircraft engine blade part clamping system according to claim 1, wherein: the first clamping device (2) is provided with a first positioning block (22) and a second positioning block (23), the first positioning block (22) is used for positioning the blade part in the vertical direction, the second positioning block (23) is provided with a positioning notch (231), and the positioning notch (231) is used for positioning the blade part in the transverse direction.
9. An aircraft engine blade part clamping system according to claim 1, wherein: the bottom of first clamping device (2) is equipped with the spout, be equipped with line rail (11) on workstation (1), line rail (11) card is in the spout, first clamping device (2) can be oriented second clamping device (3) direction reciprocating motion.
10. An aircraft engine blade part clamping system according to claim 1, wherein: the clamping area on the first clamping device (2) is a first clamping area (21), the clamping area on the second clamping device (3) is a second clamping area (31), and the first clamping area (21) and the second clamping area (31) are adjacent in the transverse direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310376181.7A CN116460631A (en) | 2023-04-10 | 2023-04-10 | Flexible clamping system for aero-engine blade part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310376181.7A CN116460631A (en) | 2023-04-10 | 2023-04-10 | Flexible clamping system for aero-engine blade part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116460631A true CN116460631A (en) | 2023-07-21 |
Family
ID=87172858
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310376181.7A Pending CN116460631A (en) | 2023-04-10 | 2023-04-10 | Flexible clamping system for aero-engine blade part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116460631A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119952505A (en) * | 2025-04-08 | 2025-05-09 | 北京航臻科技有限公司 | A design method for flexible clamping fixture of blade blank |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19755517C1 (en) * | 1997-08-29 | 1999-01-21 | Schunk Fritz Gmbh | Clamping jaws and clamping device for clamping workpieces |
| CN103934713A (en) * | 2014-05-05 | 2014-07-23 | 西北工业大学 | Needle type locating adjustable hydraulic type clamp for machining of tenon of precisely forged blade |
| CN208409214U (en) * | 2018-03-20 | 2019-01-22 | 江阴兴澄特种钢铁有限公司 | A kind of drilling cuttings sampling jig |
| CN210996602U (en) * | 2019-08-28 | 2020-07-14 | 江苏新贝斯特智能制造有限公司 | Main oil gallery processing device of medium and large automobile engine |
| CN215968413U (en) * | 2021-09-18 | 2022-03-08 | 潍坊宝润机械有限公司 | Device for processing moving blade assembly surface |
-
2023
- 2023-04-10 CN CN202310376181.7A patent/CN116460631A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19755517C1 (en) * | 1997-08-29 | 1999-01-21 | Schunk Fritz Gmbh | Clamping jaws and clamping device for clamping workpieces |
| CN103934713A (en) * | 2014-05-05 | 2014-07-23 | 西北工业大学 | Needle type locating adjustable hydraulic type clamp for machining of tenon of precisely forged blade |
| CN208409214U (en) * | 2018-03-20 | 2019-01-22 | 江阴兴澄特种钢铁有限公司 | A kind of drilling cuttings sampling jig |
| CN210996602U (en) * | 2019-08-28 | 2020-07-14 | 江苏新贝斯特智能制造有限公司 | Main oil gallery processing device of medium and large automobile engine |
| CN215968413U (en) * | 2021-09-18 | 2022-03-08 | 潍坊宝润机械有限公司 | Device for processing moving blade assembly surface |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119952505A (en) * | 2025-04-08 | 2025-05-09 | 北京航臻科技有限公司 | A design method for flexible clamping fixture of blade blank |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2763298A1 (en) | Fixture for supporting a workpiece | |
| JP5734428B2 (en) | Rotary work head device | |
| CN110216481A (en) | Numerical control vertical machine tool and method for processing valve body using it | |
| CN116460631A (en) | Flexible clamping system for aero-engine blade part | |
| CN100503152C (en) | A guide block rough milling notch clamping device | |
| CN113103031B (en) | Clamping device and processing equipment with same | |
| CN105382603B (en) | Abrasive water-jet cuts milling universal fixturing | |
| CN215392286U (en) | Hydraulic automatic clamping tool for forging rail CNC machining | |
| CN109807661B (en) | Tool clamp integrating multiple processes into one process and design method | |
| CN215903112U (en) | Numerical control milling and boring machine convenient to axial positioning | |
| CN104999311B (en) | A kind of quick clamping system for the gearshift cantilever that reverses gear | |
| CN203245612U (en) | A double-station clamp for milling pliers | |
| CN210254497U (en) | Clamp locking device for broaching connecting rod assembly surface of refrigerator compressor | |
| CN211332355U (en) | Bilateral positioning cylinder structure and machining positioning jig | |
| CN210549101U (en) | Welding jig that can switch over fast | |
| CN222244479U (en) | High-pressure-maintaining modularized fixture | |
| CN223718915U (en) | Vertical lathe crossbeam slide finish machining mould | |
| JPH0425333A (en) | Double-face machining device | |
| CN218903802U (en) | Machining tool for workpiece cutting | |
| JPH07266171A (en) | Work positioning device | |
| CN112108899B (en) | Special clamp suitable for machining L-shaped valve body and machining method | |
| CN215510096U (en) | Hydraulic clamping device for machine tool | |
| CN220498473U (en) | Tool clamp | |
| CN220161802U (en) | Four-axis clamp for processing thin cylinder body | |
| CN214186182U (en) | A squeeze clamp device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |