CN116604374B - Clamp for positioning and compacting turbine guide blade of aero-engine - Google Patents
Clamp for positioning and compacting turbine guide blade of aero-engine Download PDFInfo
- Publication number
- CN116604374B CN116604374B CN202310889864.2A CN202310889864A CN116604374B CN 116604374 B CN116604374 B CN 116604374B CN 202310889864 A CN202310889864 A CN 202310889864A CN 116604374 B CN116604374 B CN 116604374B
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- China
- Prior art keywords
- positioning
- block
- compressing assembly
- base
- compressing
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Links
- 238000003825 pressing Methods 0.000 claims description 52
- 230000006835 compression Effects 0.000 claims description 10
- 238000007906 compression Methods 0.000 claims description 10
- 238000005056 compaction Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method 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
- B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
-
- 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
- B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
- B23Q3/063—Work-clamping means adapted for holding workpieces having a special form or being made from a special material for holding turbine blades
Abstract
The invention belongs to the field of tool clamps, and particularly relates to a clamp for positioning and compacting turbine guide blades of an aeroengine. The technical proposal is as follows: the positioning and compressing device comprises a base, a first positioning and compressing assembly, a second positioning and compressing assembly, a third positioning and compressing assembly, a fourth positioning and compressing assembly and a positioning pin, wherein the first positioning and compressing assembly, the second positioning and compressing assembly, the third positioning and compressing assembly, the fourth positioning and compressing assembly and the positioning pin are fixedly arranged on the base, the first positioning and compressing assembly, the second positioning and compressing assembly, the third positioning and compressing assembly and the fourth positioning and compressing assembly are respectively positioned at the left part, the rear part, the right part and the front part of the base, the positioning pin is fixedly arranged on the right front side of the second positioning and compressing assembly, and the first positioning and compressing assembly, the second positioning and compressing assembly, the third positioning and compressing assembly and the positioning pin are used for positioning and compressing turbine guide blades of an aeroengine. The invention solves the problem that the parts are not easy to disassemble during clamping, and ensures accurate and effective positioning and compaction.
Description
Technical Field
The invention belongs to the field of tool clamps, and particularly relates to a clamp for positioning and compacting turbine guide blades of an aeroengine.
Background
The turbine guide vane of the aeroengine has a complex shape, and the turbine guide vane needs to be clamped and positioned by a clamp when being processed. Under the general circumstances, the location structure and the clamp structure of anchor clamps each independently exist and do not interfere each other, and this makes the part on the anchor clamps more dispersed, has not only increased the volume of anchor clamps, has still increased the weight of anchor clamps, and clamping dismantles all and is more difficult, and the manufacturing cost and the maintenance cost of anchor clamps all greatly increased moreover.
Disclosure of Invention
The invention provides a clamp for positioning and compacting turbine guide vanes of an aeroengine, which adopts a sliding positioning mode to position and arrange the positioning and compacting in the same component, solves the problem that parts are not easy to disassemble during clamping, ensures accurate and effective positioning, reduces the actual volume of the clamp and realizes the purpose of flexible disassembly of the parts.
The technical scheme of the invention is as follows:
the utility model provides a location and anchor clamps that compress tightly aeroengine turbine guide vane, includes base, location hold-down subassembly first, location hold-down subassembly second, location hold-down subassembly third, location hold-down subassembly fourth and locating pin are fixed to be set up on the base, location hold-down subassembly first, location hold-down subassembly second, location hold-down subassembly third and location hold-down subassembly fourth are located respectively the left part, rear portion, right part and the front portion of base, the fixed right front side that sets up in location hold-down subassembly second of locating pin, location hold-down subassembly second, location hold-down subassembly third, location hold-down subassembly fourth and locating pin are used for location and compress tightly aeroengine turbine guide vane.
Further, the clamp for positioning and compacting the turbine guide vane of the aeroengine comprises a positioning block I, a pressing plate I, a bolt I, a pressure spring I, a gasket I and an adjusting support I, wherein the positioning block I is fixedly arranged on the base, the head of the positioning block I is provided with a profiling positioning head I, and the positioning block I is provided with a transverse through groove I and a vertical through hole I; the first pressing plate is placed in the first through groove, a long round hole I is formed in the middle of the first pressing plate, the first bolt penetrates through the long round hole I and is connected with the base in a threaded mode, and the first pressure spring and the first gasket are installed on the first bolt and are located between the base and the first pressing plate; the adjusting support is in threaded connection with the base and abuts against the tail of the pressing plate I.
Further, the clamp for positioning and compacting the turbine guide vane of the aeroengine comprises a first fixing block, a support, a positioning compression rod, a first screw and a limiting pin, wherein the first fixing block is fixedly arranged on the base, two trapezoidal clamping blocks which are arranged in parallel are arranged on the first fixing block, a sliding groove is arranged between the two trapezoidal clamping blocks, one trapezoidal clamping block is provided with a first screw hole, and the other trapezoidal clamping block is provided with a sliding way; the lower part of the support is provided with a sliding block, the upper part of the support is provided with an inclined table, the sliding block is provided with a sliding rail, the sliding block is matched with the sliding groove and is matched with the sliding rail, and the positioning compression bar is fixedly arranged at the end head of the inclined table; the first screw is screwed into the first screw hole and used for positioning the support; the limiting pin is fixedly arranged on the first fixed block and located at the outlet of the sliding groove.
Further, the fixture for positioning and compacting the turbine guide vane of the aeroengine comprises a positioning block II, a pressing plate II, a bolt II, a pressure spring II, a gasket II and an adjusting support II, wherein the positioning block II is fixedly arranged on the base, the head of the positioning block II is provided with a profiling positioning head II, and the positioning block II is provided with a transverse through groove II and a vertical through hole II; the second pressing plate is placed in the second through groove, a second oblong hole is formed in the middle of the second pressing plate, a second bolt penetrates through the second oblong hole and is connected with the base in a threaded mode, and the second pressure spring and the second gasket are installed on the second bolt and are located between the base and the second pressing plate; the adjusting support II is in threaded connection with the base and props against the tail of the pressing plate II.
Further, the clamp for positioning and compacting the turbine guide vane of the aeroengine comprises a second fixing block, a rotating block, a pin shaft, a compacting pin, a pressing block and a second screw, wherein the second fixing block is fixedly arranged on the base, the rotating block is rotationally connected with the second fixing block through the pin shaft, and the compacting pin is fixedly arranged on the upper end face of the rotating block; the two ends of the pressing block are respectively provided with an upper protruding block and a lower protruding block, a third oblong hole is formed in the middle of the pressing block, a second screw penetrates into the third oblong hole and is connected with a second fixing block in a threaded mode, the upper protruding block of the pressing block is propped against the rotating block, and the lower protruding block is propped against the second fixing block.
The beneficial effects of the invention are as follows: the clamp provided by the invention adopts a sliding positioning mode to position, positions and compacts the parts in the same assembly, solves the problem that the parts are not easy to disassemble during clamping, ensures accurate and effective positioning, reduces the actual volume of the clamp, and realizes the purpose of flexible disassembly of the parts.
Drawings
FIG. 1 is a schematic view of a fixture for positioning and compressing aircraft engine turbine guide vanes;
FIG. 2 is a top view of a fixture for positioning and compressing aircraft engine turbine guide vanes;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
FIG. 4 is a schematic view of a positioning block;
FIG. 5 is a schematic view of a platen;
FIG. 6 is a schematic view of a fixed block;
FIG. 7 is a schematic view of a support;
FIG. 8 is a diagram of a second positioning block;
FIG. 9 is a schematic diagram of a second fixed block;
FIG. 10 is a schematic diagram of a rotor block;
FIG. 11 is a schematic diagram of a compact;
FIG. 12 is a schematic view of an aircraft engine turbine guide vane mounted on a fixture;
FIG. 13 is a schematic view of a turbine guide vane.
In the figure: 1 is a base, 2 is a positioning block I, 3 is a pressing plate I, 4 is a fixed block I, 5 is a limiting pin, 6 is a support, 7 is a positioning pressure bar, 8 is a positioning pin, 9 is a positioning block II, 10 is a bolt II, 11 is a pressing plate II, 12 is a pressing pin, 13 is a pressing block, 14 is a rotating block, 15 is a fixed block II, 16 is an adjusting support I, 17 is a pressure spring I, 18 is a gasket I, 19 is a bolt I, 20 is a screw I, 21 is a screw II, 22 is an adjusting support II, 23 is a profiling positioning head I, 24 is a through slot I, 25 is a through hole I, 26 is a slotted hole I, 27 is a trapezoid clamping block, 28 is a sliding block, 29 is an inclined table, 30 is a profiling positioning head II, 31 is a through slot II, 32 is a through hole II, 33 is an upper lug, 34 is a lower lug, 35 is a slotted hole III, and 36 is a turbine guide blade.
Detailed Description
As shown in fig. 1-13, a fixture for positioning and compacting turbine guide vanes of an aeroengine comprises a base 1, a first positioning compacting component, a second positioning compacting component, a third positioning compacting component, a fourth positioning compacting component and a positioning pin 8, wherein the first positioning compacting component, the second positioning compacting component, the third positioning compacting component, the fourth positioning compacting component and the positioning pin 8 are fixedly arranged on the base 1, the first positioning compacting component, the second positioning compacting component, the third positioning compacting component and the fourth positioning compacting component are respectively arranged at the left part, the rear part, the right part and the front part of the base 1, the positioning pin 8 is fixedly arranged at the right front side of the second positioning compacting component, the first positioning compacting component, the second positioning compacting component, the third positioning compacting component, the fourth positioning compacting component and the positioning pin 8 are used for positioning and compacting turbine guide vanes 36 of the aeroengine.
The positioning and compressing assembly I comprises a positioning block I2, a pressing plate I3, a bolt I19, a compression spring I17, a gasket I18 and an adjusting support I16, wherein the positioning block I2 is fixedly arranged on the base 1, the head part of the positioning block I2 is provided with a profiling positioning head I23, and the positioning block I2 is provided with a transverse through groove I24 and a vertical through hole I25; the pressing plate I3 is placed in the through groove I24, a slotted hole I26 is formed in the middle of the pressing plate I3, a bolt I19 penetrates through the slotted hole I26 and is in threaded connection with the base 1, and a pressure spring I17 and a gasket I18 are mounted on the bolt I19 and are located between the base 1 and the pressing plate I3; an adjusting support one 16 is screwed on the base 1 and abuts against the tail of the pressing plate one 3.
The positioning and compressing assembly II comprises a first fixing block 4, a support 6, a positioning compression rod 7, a first screw 20 and a limiting pin 5, wherein the first fixing block 4 is fixedly arranged on the base 1, the first fixing block 4 is provided with two trapezoidal clamping blocks 27 which are arranged in parallel, a chute is arranged between the two trapezoidal clamping blocks 27, one trapezoidal clamping block 27 is provided with a first screw hole, and the other trapezoidal clamping block 27 is provided with a slideway; the lower part of the support 6 is provided with a sliding block 28, the upper part of the support is provided with an inclined table 29, the sliding block 28 is provided with a sliding rail, the sliding block 28 and the sliding groove are matched and installed together, the sliding rail and the sliding rail are matched and installed together, and the positioning compression bar 7 is fixedly installed at the end of the inclined table 29; a first screw 20 is screwed into the first screw hole for positioning the support 6; the limiting pin 5 is fixedly arranged on the first fixed block 4 and positioned at the outlet of the chute and used for limiting the limit position of the support 6.
The positioning and compressing assembly III comprises a positioning block II 9, a pressing plate II 11, a bolt II 10, a pressure spring II, a gasket II and an adjusting support II 22, wherein the positioning block II 9 is fixedly arranged on the base 1, the head of the positioning block II 9 is provided with a profiling positioning head II 30, and the positioning block II 9 is provided with a transverse through groove II 31 and a vertical through hole II 32; the second pressing plate 11 is placed in the second through groove 31, a second oblong hole is formed in the middle of the second pressing plate 11, a second bolt 10 penetrates through the second oblong hole and is in threaded connection with the base 1, and a second compression spring and a second gasket are mounted on the second bolt 10 and are located between the base 1 and the second pressing plate 11; the second adjusting support 22 is screwed on the base 1 and abuts against the tail of the second pressing plate 11.
The positioning and compressing assembly IV comprises a second fixed block 15, a rotating block 14, a pin shaft, a compressing pin 12, a pressing block 13 and a second screw 21, wherein the second fixed block 15 is fixedly arranged on the base 1, the rotating block 14 is rotationally connected with the second fixed block 15 through the pin shaft, and the compressing pin 12 is fixedly arranged on the upper end face of the rotating block 14; the two ends of the pressing block 13 are respectively provided with an upper protruding block 33 and a lower protruding block 34, the middle part of the pressing block 13 is provided with a third oblong hole 35, a second screw 21 penetrates into the third oblong hole and is in threaded connection with the second fixed block 15, the upper protruding block 33 is propped against the upper rotating block 14, and the lower protruding block 34 is propped against the second fixed block 15.
The using process of the clamp is as follows: firstly, placing the exhaust edge end surface of a turbine guide vane 36 on a locating pin 8, wherein a profiling locating head I23 clamps the air inlet edge end surface of a lower edge plate of the turbine guide vane 36, and a profiling locating head II 30 clamps the air inlet edge end surface of an upper edge plate of the turbine guide vane 36; then, the first bolt 19 is screwed down to press the first pressing plate 3 on the exhaust edge end face of the lower edge plate of the turbine guide vane 36, and the second bolt 10 is screwed down to press the second pressing plate 11 on the exhaust edge end face of the upper edge plate of the turbine guide vane 36; thereafter, the support 6 is pushed to slide forwards, the positioning pressure rod 7 is pressed above one side of the turbine guide vane 36, and the first screw 20 is screwed to position the support 6; then, the screw II 21 is screwed down to enable the upper protruding block 33 of the pressing block 13 to press against the rotating block 14, and the rotating block 14 drives the pressing pin 12 to press the other side of the turbine guide vane 36; the positioning pin 8 is used as a Z-axis positioning point of the turbine guide vane 36, the first pressing plate 3 and the second pressing plate 11 realize the compression of the turbine guide vane 36 in the Z-axis direction, the first profiling positioning head 23 and the second profiling positioning head 30 realize the Y-axis positioning of the turbine guide vane 36, the positioning pressing rod 7 and the compression pin 12 form the X-axis positioning of the turbine guide vane 36, and the control positioning of six degrees of freedom of the turbine guide vane 36 is realized; carrying out subsequent processing; after the processing is completed, the part can be detached by loosening the first bolt 19, the second bolt 10, the first screw 20 and the second screw 21.
Claims (1)
1. The fixture is characterized by comprising a base, a first positioning and compressing assembly, a second positioning and compressing assembly, a third positioning and compressing assembly, a fourth positioning and compressing assembly and a positioning pin, wherein the first positioning and compressing assembly, the second positioning and compressing assembly, the third positioning and compressing assembly, the fourth positioning and compressing assembly and the positioning pin are fixedly arranged on the base, the first positioning and compressing assembly, the second positioning and compressing assembly, the third positioning and compressing assembly and the fourth positioning and compressing assembly are respectively positioned at the left part, the rear part, the right part and the front part of the base, the positioning pin is fixedly arranged at the right front side of the second positioning and compressing assembly, and the first positioning and compressing assembly, the third positioning and compressing assembly, the fourth positioning and compressing assembly and the positioning pin are used for positioning and compressing the turbine guide blade of the aeroengine;
the positioning and compressing assembly I comprises a positioning block I, a pressing plate I, a bolt I, a pressure spring I, a gasket I and an adjusting support I, wherein the positioning block I is fixedly arranged on the base; the first pressing plate is placed in the first through groove, a long round hole I is formed in the middle of the first pressing plate, the first bolt penetrates through the long round hole I and is connected with the base in a threaded mode, and the first pressure spring and the first gasket are installed on the first bolt and are located between the base and the first pressing plate; the adjusting support I is in threaded connection with the base and props against the tail of the pressing plate I;
the positioning and compressing assembly II comprises a fixing block I, a support, a positioning compression bar, a screw I and a limiting pin, wherein the fixing block I is fixedly arranged on the base, the fixing block I is provided with two trapezoidal clamping blocks which are arranged in parallel, a sliding groove is arranged between the two trapezoidal clamping blocks, one trapezoidal clamping block is provided with a screw hole I, and the other trapezoidal clamping block is provided with a sliding way; the lower part of the support is provided with a sliding block, the upper part of the support is provided with an inclined table, the sliding block is provided with a sliding rail, the sliding block is matched with the sliding groove and is matched with the sliding rail, and the positioning compression bar is fixedly arranged at the end head of the inclined table; the first screw is screwed into the first screw hole and used for positioning the support; the limiting pin is fixedly arranged on the first fixed block and positioned at the outlet of the sliding groove;
the positioning and compressing assembly III comprises a positioning block II, a pressing plate II, a bolt II, a pressure spring II, a gasket II and an adjusting support II, wherein the positioning block II is fixedly arranged on the base; the second pressing plate is placed in the second through groove, a second oblong hole is formed in the middle of the second pressing plate, a second bolt penetrates through the second oblong hole and is connected with the base in a threaded mode, and the second pressure spring and the second gasket are installed on the second bolt and are located between the base and the second pressing plate; the second adjusting support is in threaded connection with the base and props against the tail of the second pressing plate;
the positioning and compressing assembly IV comprises a fixing block II, a rotating block, a pin shaft, a compressing pin, a pressing block and a screw II, wherein the fixing block II is fixedly arranged on the base, the rotating block is rotationally connected with the fixing block II through the pin shaft, and the compressing pin is fixedly arranged on the upper end surface of the rotating block; the two ends of the pressing block are respectively provided with an upper protruding block and a lower protruding block, a third oblong hole is formed in the middle of the pressing block, a second screw penetrates into the third oblong hole and is connected with a second fixing block in a threaded mode, the upper protruding block of the pressing block is propped against the rotating block, and the lower protruding block is propped against the second fixing block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310889864.2A CN116604374B (en) | 2023-07-20 | 2023-07-20 | Clamp for positioning and compacting turbine guide blade of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310889864.2A CN116604374B (en) | 2023-07-20 | 2023-07-20 | Clamp for positioning and compacting turbine guide blade of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116604374A CN116604374A (en) | 2023-08-18 |
| CN116604374B true CN116604374B (en) | 2023-09-15 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310889864.2A Active CN116604374B (en) | 2023-07-20 | 2023-07-20 | Clamp for positioning and compacting turbine guide blade of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116604374B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117001087A (en) * | 2023-09-28 | 2023-11-07 | 中国航发沈阳黎明航空发动机有限责任公司 | Blade clamp capable of achieving electric spark machining and numerical control milling |
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| CN115533691A (en) * | 2022-10-24 | 2022-12-30 | 中国航发沈阳黎明航空发动机有限责任公司 | Low-pressure turbine guide blade slow-in grinding self-adaptive machining clamp and using method |
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| ITBO20070673A1 (en) * | 2007-10-03 | 2009-04-04 | Corima Internat Machinery S R | MACHINE FOR THE RECEPTION OF THE PAPER SHEETS OF WINDING OF PRODUCTS, IN PARTICULAR OF BATTERIES OF COVERS |
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| CN103878608A (en) * | 2014-01-30 | 2014-06-25 | 无锡透平叶片有限公司 | Clamp used for processing aviation thin-wall blade pitch |
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| CN107598608A (en) * | 2017-10-12 | 2018-01-19 | 无锡透平叶片有限公司 | Grip device for turbine blade leading edge alloy sheet milling |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN116604374A (en) | 2023-08-18 |
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