CN116587024B - Self-adaptive clamp for production of aero-engine double-positioning reference table blade - Google Patents
Self-adaptive clamp for production of aero-engine double-positioning reference table blade Download PDFInfo
- Publication number
- CN116587024B CN116587024B CN202310868183.8A CN202310868183A CN116587024B CN 116587024 B CN116587024 B CN 116587024B CN 202310868183 A CN202310868183 A CN 202310868183A CN 116587024 B CN116587024 B CN 116587024B
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- positioning
- ball screw
- adaptive
- steel ball
- blade
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 5
- 229910000831 Steel Inorganic materials 0.000 claims abstract description 58
- 239000010959 steel Substances 0.000 claims abstract description 58
- 230000003044 adaptive effect Effects 0.000 claims description 7
- 230000009977 dual effect Effects 0.000 claims description 3
- 238000003754 machining Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 208000017740 grade III prostatic intraepithelial neoplasia Diseases 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
-
- 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
- B23Q2703/00—Work clamping
- B23Q2703/02—Work clamping means
- B23Q2703/10—Devices for clamping workpieces of a particular form or made from a particular material
-
- 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 invention belongs to the technical field of part clamping and positioning, and particularly relates to a self-adaptive clamp for producing an aero-engine double-positioning reference table blade. The technical scheme of the invention is as follows: the self-adaptive clamp for the production of the aeroengine double-positioning reference table blade comprises a main positioning end clamp and an auxiliary positioning end clamp, wherein the main positioning end clamp comprises a first base, a first plane moving direction steel ball screw, a second plane moving direction steel ball screw, a self-adaptive rotating block and a first positioning pin, the auxiliary positioning end clamp comprises a second base, a third plane moving direction steel ball screw, a fourth plane moving direction steel ball screw, a first jackscrew, a second jackscrew and a second positioning pin, and the main positioning end clamp and the auxiliary positioning end clamp are used for positioning the double-positioning reference table of the blade. The self-adaptive clamp for producing the aero-engine double-positioning reference table blade can carry out self-adaptive clamping according to the deformation state of the positioning reference surface of the blade so as to ensure that the processing size of the blade is qualified.
Description
Technical Field
The invention belongs to the technical field of part clamping and positioning, and particularly relates to a self-adaptive clamp for producing an aero-engine double-positioning reference table blade.
Background
The positioning reference surface of the aero-engine double positioning reference table blade cannot be kept stable in flatness in the machining process, the positioning reference surface is deformed due to machining stress in the machining process of the previous working procedure, and machining dimension out of tolerance can be caused when the deformed positioning reference surface is used for clamping parts in the subsequent working procedure.
Disclosure of Invention
The invention provides a self-adaptive clamp for producing an aero-engine double-positioning reference table blade, which can carry out self-adaptive clamping according to the deformation state of a positioning reference surface of the blade so as to ensure that the processing size of the blade is qualified.
The technical scheme of the invention is as follows:
the self-adaptive clamp for producing the aeroengine double-positioning reference table blade comprises a main positioning end clamp and an auxiliary positioning end clamp, wherein the main positioning end clamp comprises a first base, a first plane moving steel ball screw, a second plane moving steel ball screw, a self-adaptive rotating block and a first positioning pin, a first clamping table is arranged at the left end of the first base, a square positioning groove I which is concave is arranged at the first clamping table, a first thread is arranged on the top wall of the first positioning groove, a second thread is arranged on the side wall of the first positioning groove, a rotating groove is arranged on the bottom wall of the first positioning groove, the first plane moving steel ball screw is screwed into the first thread, the second plane moving steel ball screw is screwed into the second thread, the self-adaptive rotating block is placed in the rotating groove, and the first positioning pin is arranged inside the first positioning groove and positioned on the inner side of the rotating groove; the auxiliary positioning end clamp comprises a second base, a third plane moving steel ball screw, a fourth plane moving steel ball screw, a first jackscrew, a second jackscrew and a second positioning pin, wherein the right end of the second base is provided with a second clamping table, the second clamping table is provided with a positioning groove II with a side opening, the top wall of the second positioning groove is provided with a third thread, the bottom wall of the second positioning groove is provided with a fourth thread, the third plane moving steel ball screw is screwed into the third thread, the fourth plane moving steel ball screw is screwed into the fourth thread, the first jackscrew is arranged below the fourth plane moving steel ball screw, the second jackscrew is arranged on the side of the fourth plane moving steel ball screw, and the second positioning pin is arranged on the side wall of the second positioning groove; the main positioning end clamp and the auxiliary positioning end clamp are used for positioning the double positioning reference tables of the blades.
Further, the self-adaptive clamp for producing the aero-engine double-positioning reference table blade takes the rotation center lines of the main positioning end clamp and the auxiliary positioning end clamp as X-axis, the Y-axis is parallel to the upper end surface of the clamping table I, and the Z-axis is perpendicular to the XY plane.
Further, the self-adaptive clamp for producing the aero-engine double-positioning reference table blade is characterized in that the rotary groove is in a semi-cylindrical shape, and the axis of the rotary groove is arranged along the Y-axis direction; the self-adaptive rotating block is in a semi-cylindrical shape and is matched with the rotating groove to be installed together; the bottom wall of the first positioning groove is provided with two positioning pins III which are respectively used for positioning the two ends of the self-adaptive rotating block so as to limit the movement of the self-adaptive rotating block in the Y direction and only keep the rotational freedom degree of the self-adaptive rotating block around the Y direction.
Further, the self-adaptive clamp for producing the aeroengine double-positioning reference table blade ensures that the top end of the plane moving steel ball screw rod I and the self-adaptive rotating block can synchronously rotate when the main positioning reference table of the blade is clamped, and simultaneously limits the movement of the main positioning reference table of the blade in the Z direction.
Further, the self-adaptive clamp for producing the aero-engine double-positioning reference table blade is characterized in that a positioning pin is used for limiting the movement of a main positioning reference table of the blade in the X direction; the side walls of the plane moving steel ball screw II and the positioning groove I are used for limiting the movement of the main positioning reference table of the blade in the Y direction and the rotation freedom degree around the Z axis.
Further, the self-adaptive clamp for producing the aero-engine double-positioning reference table blade is characterized in that a plane moving direction steel ball screw rod III and a plane moving direction steel ball screw rod IV are coaxially arranged and used for limiting the movement of the auxiliary positioning reference table of the blade in the Z direction.
Furthermore, the self-adaptive clamp for producing the aero-engine double-positioning reference table blade is characterized in that the second positioning pin is used for limiting the movement of the auxiliary positioning reference table of the blade in the Y direction.
The beneficial effects of the invention are as follows: the top end of the plane moving direction steel ball screw rod can rotate 360 degrees, the self-adaptive rotating block can rotate around the rotating center of the self-adaptive rotating block, and the self-adaptive clamping can be carried out according to the deformation state of the positioning reference surface of the blade, so that the machining size of the blade is ensured to be qualified.
Drawings
FIG. 1 is a schematic view of a production adaptive clamp for an aircraft engine dual positioning datum stage blade;
FIG. 2 is a schematic view of a main locating end fixture;
FIG. 3 is a front view of the secondary locating end fixture;
FIG. 4 is a schematic diagram of an adaptive rotating block;
FIG. 5 is a schematic view of a blade clamping state of an adaptive clamp for producing an aero-engine double-positioning reference table blade;
in the figure: 1 is a base I, 2 is a clamping table I, 3 is a plane moving direction steel ball screw rod I, 4 is a plane moving direction steel ball screw rod II, 5 is a positioning pin III, 6 is a self-adaptive rotating block, 7 is a positioning pin I, 11 is a base II, 12 is a clamping table II, 13 is a plane moving direction steel ball screw rod III, 14 is a plane moving direction steel ball screw rod IV, 15 is a positioning pin II, 16 is a jackscrew II, 17 is a jackscrew I, and 20 is a blade.
Detailed Description
As shown in figures 1-4, the self-adaptive clamp for producing the aeroengine double-positioning reference table blade comprises a main positioning end clamp and an auxiliary positioning end clamp, wherein the rotation center line of the main positioning end clamp and the auxiliary positioning end clamp is taken as an X axis, a Y axis is parallel to the upper end surface of a clamping table I, and a Z axis is perpendicular to an XY plane.
The main positioning end clamp comprises a first base 1, a first plane moving steel ball screw 3, a second plane moving steel ball screw 4, a self-adaptive rotating block 6 and a first positioning pin 7, wherein the left end of the first base 1 is provided with a first clamping table 2, the first clamping table 2 is provided with a concave square positioning groove I, the top wall of the positioning groove I is provided with a first thread, the side wall of the positioning groove I is provided with a second thread, the bottom wall of the positioning groove I is provided with a rotating groove, the first plane moving steel ball screw 3 is screwed into the first thread, the second plane moving steel ball screw 4 is screwed into the second thread, the self-adaptive rotating block 6 is placed in the rotating groove, and the first positioning pin 7 is arranged inside the positioning groove I and is positioned on the inner side of the rotating groove; the rotary groove is in a semi-cylindrical shape, and the axis of the rotary groove is arranged along the Y-axis direction; the self-adaptive rotating block 6 is in a semi-cylindrical shape, and the self-adaptive rotating block 6 and the rotating groove are matched and installed together; two locating pins III 5 are arranged on the bottom wall of the first locating groove, and the two locating pins III 5 are respectively used for locating two ends of the self-adaptive rotating block 6 so as to limit the movement of the self-adaptive rotating block 6 in the Y direction, and only the rotational freedom degree of the self-adaptive rotating block 6 around the Y direction is reserved. The projection of the rotation center of the top end of the plane moving direction steel ball screw 3 and the projection of the rotation center of the self-adaptive rotating block 6 on the XOY plane are collinear, so that the top end of the plane moving direction steel ball screw 3 and the self-adaptive rotating block 6 can synchronously rotate when the main positioning reference table of the blade 20 is clamped, and meanwhile, the movement of the main positioning reference table of the blade 20 in the Z direction is limited. The first positioning pin 7 is used for limiting the movement of the main positioning reference table of the blade 20 in the X direction; the side walls of the plane moving direction steel ball screw rod II 4 and the positioning groove I are used for limiting the movement of the main positioning reference table of the blade 20 in the Y direction and the rotation freedom degree around the Z axis.
The auxiliary positioning end clamp comprises a second base 11, a third plane moving steel ball screw rod 13, a fourth plane moving steel ball screw rod 14, a first jackscrew 17, a second jackscrew 16 and a second positioning pin 15, wherein a second clamping table 12 is arranged at the right end of the second base 11, a positioning groove with an opening on the side surface is arranged on the second clamping table 12, a third thread is arranged on the top wall of the second positioning groove, a fourth thread is arranged on the bottom wall of the second positioning groove, the third plane moving steel ball screw rod 13 is screwed into the third thread, the fourth plane moving steel ball screw rod 14 is screwed into the fourth thread, the first jackscrew 17 is arranged below the fourth plane moving steel ball screw rod 14, the second jackscrew 16 is arranged on the side of the fourth plane moving steel ball screw rod 14, and the second positioning pin 15 is arranged on the side wall of the second positioning groove; the plane moving direction steel ball screw III 13 and the plane moving direction steel ball screw IV 14 are coaxially arranged and are used for limiting the movement of the auxiliary positioning reference table of the blade 20 in the Z direction; the second positioning pin 15 is used to restrict the movement of the sub positioning reference stage of the blade 20 in the Y direction.
The model of the plane moving direction steel ball screw is PT16B-1220.
In the using process, as shown in fig. 5, the plane moving direction steel ball screw four 14 is adjusted to a specified height, and the plane moving direction steel ball screw four 14 is fixed through the jackscrew one 17 and the jackscrew two 16; placing a main positioning reference table of the blade 20 into a positioning groove I of a main positioning end clamp, placing the main positioning reference table on the self-adaptive rotating block 6, and tightly attaching the main positioning reference table of the blade 20 to a positioning pin I7; moving the auxiliary positioning end clamp to enable the positioning groove II to be aligned with an auxiliary positioning reference table of the blade 20, and placing the auxiliary positioning reference table of the blade 20 on the plane moving direction steel ball screw rod IV 14; the side surface of the main positioning reference table of the blade 20 is abutted against the side wall of the first positioning groove, the side surface of the auxiliary positioning reference table of the blade 20 is abutted against the second positioning pin 15, the first plane moving direction steel ball screw rod 3 and the third plane moving direction steel ball screw rod 13 are respectively screwed up, and finally the second plane moving direction steel ball screw rod 4 is screwed up, so that the blade 20 can be clamped in a self-adaptive manner; and performing subsequent processing.
Claims (7)
1. The self-adaptive clamp for the production of the aeroengine double-positioning reference table blade is characterized by comprising a main positioning end clamp and an auxiliary positioning end clamp, wherein the main positioning end clamp comprises a first base, a first plane moving steel ball screw, a second plane moving steel ball screw, a self-adaptive rotating block and a first positioning pin; the auxiliary positioning end clamp comprises a second base, a third plane moving steel ball screw, a fourth plane moving steel ball screw, a first jackscrew, a second jackscrew and a second positioning pin, wherein the right end of the second base is provided with a second clamping table, the second clamping table is provided with a positioning groove II with a side opening, the top wall of the second positioning groove is provided with a third thread, the bottom wall of the second positioning groove is provided with a fourth thread, the third plane moving steel ball screw is screwed into the third thread, the fourth plane moving steel ball screw is screwed into the fourth thread, the first jackscrew is arranged below the fourth plane moving steel ball screw, the second jackscrew is arranged on the side of the fourth plane moving steel ball screw, and the second positioning pin is arranged on the side wall of the second positioning groove; the main positioning end clamp and the auxiliary positioning end clamp are used for positioning the double positioning reference tables of the blades.
2. The adaptive jig for producing an aircraft engine double-positioning reference table blade according to claim 1, wherein the center line of rotation of the main positioning end jig and the auxiliary positioning end jig is taken as an X axis, the Y axis is parallel to the upper end face of the first clamping table, and the Z axis is perpendicular to the XY plane.
3. The adaptive clamp for producing an aeroengine double positioning reference table blade according to claim 2, wherein the rotary groove is in a semi-cylindrical shape, and an axis of the rotary groove is arranged along a Y-axis direction; the self-adaptive rotating block is in a semi-cylindrical shape and is matched with the rotating groove to be installed together; the bottom wall of the first positioning groove is provided with two positioning pins III which are respectively used for positioning the two ends of the self-adaptive rotating block so as to limit the movement of the self-adaptive rotating block in the Y direction and only keep the rotational freedom degree of the self-adaptive rotating block around the Y direction.
4. The self-adaptive clamp for producing the aeroengine double-positioning reference table blade according to claim 3, wherein the projection of the rotation center of the top end of the plane moving direction steel ball screw rod I and the projection of the rotation center of the self-adaptive rotation block on the XOY plane are collinear, so that the top end of the plane moving direction steel ball screw rod I and the self-adaptive rotation block can synchronously rotate when the main positioning reference table of the blade is clamped, and meanwhile, the movement of the main positioning reference table of the blade in the Z direction is limited.
5. The adaptive fixture for producing an aircraft engine dual positioning reference stage blade according to claim 2, wherein the positioning pin is used for limiting the movement of the main positioning reference stage of the blade in the X direction; the side walls of the plane moving steel ball screw II and the positioning groove I are used for limiting the movement of the main positioning reference table of the blade in the Y direction and the rotation freedom degree around the Z axis.
6. The self-adaptive clamp for producing the double-positioning reference table blade of the aeroengine, according to claim 2, wherein the plane moving direction steel ball screw three and the plane moving direction steel ball screw four are coaxially arranged, and are used for limiting the movement of the auxiliary positioning reference table of the blade in the Z direction.
7. The adaptive clamp for producing an aircraft engine dual positioning reference table blade of claim 2, wherein the second positioning pin is used to limit movement of the auxiliary positioning reference table of the blade in the Y-direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310868183.8A CN116587024B (en) | 2023-07-17 | 2023-07-17 | Self-adaptive clamp for production of aero-engine double-positioning reference table blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310868183.8A CN116587024B (en) | 2023-07-17 | 2023-07-17 | Self-adaptive clamp for production of aero-engine double-positioning reference table blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116587024A CN116587024A (en) | 2023-08-15 |
| CN116587024B true CN116587024B (en) | 2023-09-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310868183.8A Active CN116587024B (en) | 2023-07-17 | 2023-07-17 | Self-adaptive clamp for production of aero-engine double-positioning reference table blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116587024B (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201645206U (en) * | 2010-01-21 | 2010-11-24 | 西北工业大学 | Blade NC Machining Precision Positioning Fixture |
| JP2011073131A (en) * | 2009-09-30 | 2011-04-14 | Nasada:Kk | Resin filling holding device of blade, resin filling solidification method of blade, resin filling solidification processing method of blade, resin filling solidification processing device of long size blade and resin filling solidification processing method of long size blade |
| CN102357813A (en) * | 2011-09-09 | 2012-02-22 | 山东大学 | Fixture for processing and detecting blade of aircraft engine |
| CN102513587A (en) * | 2011-12-28 | 2012-06-27 | 四川成发航空科技股份有限公司 | Method for machining flat groove on front edge of low-pressure air intake guide blade of aeroengine |
| CN102615534A (en) * | 2012-04-10 | 2012-08-01 | 西北工业大学 | Hydraulic fixture used for machining precision forging blade tenon root |
| CN102773733A (en) * | 2012-07-18 | 2012-11-14 | 西安航空动力股份有限公司 | Method and clamp for moulding surface positioning clamping of finish forge blade |
| EP2548694A1 (en) * | 2011-07-20 | 2013-01-23 | MTU Aero Engines AG | Device and method for tensioning a workpiece |
| EP3800326A1 (en) * | 2019-10-02 | 2021-04-07 | Raytheon Technologies Corporation | Ceramic matrix composite rotor blade attachment and method of manufacture therefor |
| CN114749954A (en) * | 2022-04-13 | 2022-07-15 | 西安三航动力科技有限公司 | Self-adaptive clamping device for craft platform of aviation blade tip |
-
2023
- 2023-07-17 CN CN202310868183.8A patent/CN116587024B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011073131A (en) * | 2009-09-30 | 2011-04-14 | Nasada:Kk | Resin filling holding device of blade, resin filling solidification method of blade, resin filling solidification processing method of blade, resin filling solidification processing device of long size blade and resin filling solidification processing method of long size blade |
| CN201645206U (en) * | 2010-01-21 | 2010-11-24 | 西北工业大学 | Blade NC Machining Precision Positioning Fixture |
| EP2548694A1 (en) * | 2011-07-20 | 2013-01-23 | MTU Aero Engines AG | Device and method for tensioning a workpiece |
| CN102357813A (en) * | 2011-09-09 | 2012-02-22 | 山东大学 | Fixture for processing and detecting blade of aircraft engine |
| CN102513587A (en) * | 2011-12-28 | 2012-06-27 | 四川成发航空科技股份有限公司 | Method for machining flat groove on front edge of low-pressure air intake guide blade of aeroengine |
| CN102615534A (en) * | 2012-04-10 | 2012-08-01 | 西北工业大学 | Hydraulic fixture used for machining precision forging blade tenon root |
| CN102773733A (en) * | 2012-07-18 | 2012-11-14 | 西安航空动力股份有限公司 | Method and clamp for moulding surface positioning clamping of finish forge blade |
| EP3800326A1 (en) * | 2019-10-02 | 2021-04-07 | Raytheon Technologies Corporation | Ceramic matrix composite rotor blade attachment and method of manufacture therefor |
| CN114749954A (en) * | 2022-04-13 | 2022-07-15 | 西安三航动力科技有限公司 | Self-adaptive clamping device for craft platform of aviation blade tip |
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| Publication number | Publication date |
|---|---|
| CN116587024A (en) | 2023-08-15 |
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