Semi-surrounding clamping device for machining aircraft engine ring piece
By designing a semi-encirclement clamping device, using ring grooves, clamping cylinders and rotating components, the problem of reduced machining surface caused by ring clamping devices of the aircraft engine ring parts in the prior art is solved, and efficient machining and flexible adjustment of ring parts is achieved , improves processing efficiency.
Patent Information
- Application Number
- CN202421045322.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-14
- Publication Date
- 2024-12-24
- Estimated Expiration
- 2034-05-14
AI Technical Summary
The existing aircraft engine ring clamping device clamps the inner and outer sides of the ring clamping, resulting in a reduction of machining surfaces and affecting machining efficiency.
A semi-encirclement clamping device is designed, including a base plate, a placement plate, a rotating assembly and a semi-encirclement clamping assembly. Through the combination of an ring groove, a clamping cylinder and a clamping block, the semi-encirclement clamping on the inner circumference of the ring member is realized. , and adjust the direction of the clamping assembly through the rotating shaft and bearing to adapt to the clamping needs of different angles.
Through the semi-encirclement clamping technology, the upper and outer machining surfaces of the ring are completely exposed, which improves processing efficiency and is convenient for use through the rotation adjustment function.
Smart Images
Figure CN222221897U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of aircraft engine ring processing, and in particular relates to a semi-enclosed clamping device for aircraft engine ring processing. Background Art
[0002] Aircraft engine rings are one of the key structural components in aircraft engines. They usually withstand high temperature, high pressure, high corrosion and high-intensity working environments. The functions of rings in the engine include supporting, connecting and fixing other components, such as turbine discs, compressor discs, etc. They play a vital role in the performance and reliability of the engine.
[0003] Aircraft engine rings need to be clamped and fixed using a clamping device during processing, but most of the existing clamping devices fully surround and clamp the inside and outside of the aircraft engine rings or press the upper end surface to fix them, resulting in a reduction in the machinable surface of the aircraft engine rings, affecting the processing and use of the aircraft engine rings. For this reason, we propose a semi-enclosed clamping device for processing aircraft engine rings. Utility Model Content
[0004] The utility model aims to provide a semi-enclosed clamping device for machining an aircraft engine ring to solve the problems raised in the above-mentioned background technology.
[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a semi-enclosed clamping device for processing aircraft engine rings, comprising a base plate, the base plate is provided with a placement plate, the placement plate is provided with a ring groove for clamping the lower part of the aircraft engine ring, the placement plate is provided with a rotating assembly located in the middle of the inner side of the aircraft engine ring, the rotating assembly is provided with semi-enclosed clamping assemblies distributed in an annular array, and the semi-enclosed clamping assemblies distributed in an annular array abut against and support the inner circumference of the aircraft engine ring.
[0006] Preferably, the placement plate is a circular plate, and the annular groove and the placement plate are concentrically arranged.
[0007] Preferably, the depth of the annular groove is less than one eighth of the height of the aircraft engine ring.
[0008] Preferably, the rotating assembly comprises a rotating shaft, a bearing and a rotating disk;
[0009] The rotating shaft is arranged in the middle of the placing plate through the bearing, the rotating disk is arranged at the upper end of the rotating shaft, and the bottom end surface of the rotating disk is higher than the upper end surface of the placing plate.
[0010] Preferably, the semi-enclosed clamping assembly comprises a clamping cylinder and a clamping block;
[0011] The clamping cylinder is arranged on the rotating disk, and the clamping block is arranged at the output end of the clamping cylinder.
[0012] Preferably, a side surface of the clamping block facing the inner circumference of the aircraft engine ring is an arc-shaped surface adapted to the inner circumference of the aircraft engine ring.
[0013] Preferably, a step is provided on the lower middle portion of the inner circumference of the aircraft engine ring, and a step snap-in is provided on the clamping block at a position corresponding to the step facing the aircraft engine ring, and the step snap-in on the clamping block is snapped onto the step on the inner circumference of the aircraft engine ring.
[0014] Preferably, the upper end surface of the clamping block is flush with one half of the height of the aircraft engine ring.
[0015] Compared with the prior art, the beneficial effects of the utility model are:
[0016] 1. The utility model is provided with an annular groove, a clamping cylinder, a clamping block and a step bayonet, and the step bayonet on the clamping block is clamped on the step on the inner circumference side of the aircraft engine ring, and the upper end surface of the clamping block is flush with one-half of the height of the aircraft engine ring. When in use, the aircraft engine ring is placed in the annular groove, so that the lower part of the aircraft engine ring is positioned and clamped in the annular groove, and then the clamping cylinder is started, and the clamping cylinder drives the clamping block to extend, so that the arc surface of the clamping block contacts the inner circumference side of the aircraft engine ring, and the step bayonet on the clamping block is clamped on the step on the inner circumference side of the aircraft engine ring, so that the clamping block semi-encloses and clamps the aircraft engine ring, and is clamped and fixed by the combination of the annular groove and the clamping block, and the height of the clamping block is reduced, so that the upper part and the outer processing surface of the aircraft engine ring are completely exposed, which is convenient for processing and use, and improves processing efficiency;
[0017] 2. The utility model is provided with a rotating shaft, a bearing and a rotating disk. When in use, the rotating disk can be rotated manually so that the rotating disk can rotate on the placement plate through the rotating shaft and the bearing, thereby adjusting the direction of the semi-enclosed clamping assembly, which is convenient for adjustment and use. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;
[0019] Figure 2 It is a cross-sectional structural schematic diagram of the utility model;
[0020] Figure 3 It is a partial three-dimensional structural schematic diagram of the utility model;
[0021] Figure 4 It is a partial three-dimensional structural schematic diagram of the utility model.
[0022] In the figure: 1, bottom plate; 2, placement plate; 3, aircraft engine ring; 301, step; 4, ring groove; 5, rotating assembly; 501, rotating shaft; 502, bearing; 503, rotating disk; 6, semi-enclosed clamping assembly; 601, clamping cylinder; 602, clamping block; 603, step bayonet. DETAILED DESCRIPTION
[0023] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0024] See also Figure 1-Figure 4 The semi-enclosed clamping device for processing an aircraft engine ring provided by the utility model comprises a bottom plate 1, the bottom plate 1 is provided with a placing plate 2, the placing plate 2 is a circular plate, the annular groove 4 and the placing plate 2 are arranged concentrically, the placing plate 2 is provided with an annular groove 4 for clamping the lower part of the aircraft engine ring 3, the depth of the annular groove 4 is less than one eighth of the height of the aircraft engine ring 3, and the lower part of the aircraft engine ring 3 is clamped in the annular groove 4, and sufficient height is reserved for clamping, and a rotating assembly 5 is arranged on the placing plate 2 at the middle part of the inner side of the aircraft engine ring 3, and the rotating assembly 5 comprises a rotating shaft 501, a bearing 502 and a rotating disk 503; the rotating shaft 501 is arranged in the middle part of the placing plate 2 through the bearing 502, the rotating disk 503 is arranged at the upper end of the rotating shaft 501, and the bottom end surface of the rotating disk 503 is higher than the upper end surface of the placing plate 2;
[0025] The rotating assembly 5 is provided with semi-enclosed clamping assemblies 6 distributed in an annular array, and the semi-enclosed clamping assemblies 6 distributed in an annular array abut against and support the inner circumference of the aircraft engine ring 3. The semi-enclosed clamping assembly 6 includes a clamping cylinder 601 and a clamping block 602; the clamping cylinder 601 is arranged on the rotating disk 503, and the clamping block 602 is arranged at the output end of the clamping cylinder 601. The side surface of the clamping block 602 facing the inner circumference of the aircraft engine ring 3 is an arc surface adapted to the inner circumference of the aircraft engine ring 3, and a step 301 is arranged at the middle and lower part of the inner circumference of the aircraft engine ring 3. A step bayonet 603 is opened on the clamping block 602 at a position corresponding to the step 301 of the aircraft engine ring 3, and the step bayonet 603 on the clamping block 602 is clamped on the step 301 on the inner circumference of the aircraft engine ring 3, and the upper end surface of the clamping block 602 is flush with half of the height of the aircraft engine ring 3.
[0026] The utility model is provided with an annular groove 4, a clamping cylinder 601, a clamping block 602 and a step bayonet 603, and the step bayonet 603 on the clamping block 602 is clamped on the step 301 on the inner circumference of the aircraft engine ring 3, and the upper end surface of the clamping block 602 is flush with one-half of the height of the aircraft engine ring 3. When in use, the aircraft engine ring 3 is placed in the annular groove 4, so that the lower part of the aircraft engine ring 3 is positioned and clamped in the annular groove 4, and then the clamping cylinder 601 is started, and the clamping cylinder 601 drives the clamping block 602 is extended, so that the arc surface of the clamping block 602 contacts the inner circumference of the aircraft engine ring 3, and the step bayonet 603 on the clamping block 602 is clamped on the step 301 on the inner circumference of the aircraft engine ring 3, so that the clamping block 602 half surrounds and clamps the aircraft engine ring 3, and the combination of the annular groove 4 and the clamping block 602 clamps and fixes the aircraft engine ring 3, and the height of the clamping block 602 is reduced, so that the upper part and the outer processing surface of the aircraft engine ring 3 are completely exposed, which is convenient for processing and use, and improves processing efficiency;
[0027] The utility model is provided with a rotating shaft 501, a bearing 502 and a rotating disk 503. When in use, the rotating disk 503 can be rotated manually so that the rotating disk 503 rotates on the placement plate 2 through the rotating shaft 501 and the bearing 502, thereby adjusting the direction of the semi-enclosed clamping assembly 6, which is convenient for adjustment and use.
[0028] In summary, the method for using the semi-enclosed clamping device for processing aircraft engine rings provided in this embodiment is as follows: when in use, the aircraft engine ring 3 is placed in the annular groove 4 so that the lower part of the aircraft engine ring 3 is positioned and clamped in the annular groove 4, and the rotating disk 503 can be manually rotated to rotate the rotating disk 503 on the placement plate 2 through the rotating shaft 501 and the bearing 502, thereby adjusting the direction of the semi-enclosed clamping assembly 6, and then the clamping cylinder 601 is started, and the clamping cylinder 601 drives the clamping block 602 to extend, so that the arc surface of the clamping block 602 contacts the inner circumference of the aircraft engine ring 3, and the step bayonet 603 on the clamping block 602 is clamped on the step 301 on the inner circumference of the aircraft engine ring 3, so that the clamping block 602 semi-encloses and clamps the aircraft engine ring 3, and is clamped and fixed by the combination of the annular groove 4 and the clamping block 602.
[0029] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A semi-enclosed clamping device for processing aircraft engine ring parts, characterized in that: The invention comprises a bottom plate (1), the bottom plate (1) being provided with a placement plate (2), the placement plate (2) being provided with an annular groove (4) for clamping the lower part of an aircraft engine ring (3), the placement plate (2) being provided with a rotating assembly (5) located at the middle part of the inner side of the aircraft engine ring (3), the rotating assembly (5) being provided with semi-enclosed clamping assemblies (6) distributed in an annular array, the semi-enclosed clamping assemblies (6) distributed in an annular array abutting against and supporting the inner circumference of the aircraft engine ring (3).
2. A semi-enclosed clamping device for machining an aircraft engine ring according to claim 1, characterized in that: The placement plate (2) is a circular plate, and the annular groove (4) and the placement plate (2) are arranged concentrically.
3. The semi-enclosed clamping device for machining an aircraft engine ring according to claim 1, characterized in that: The depth of the annular groove (4) is less than one eighth of the height of the aircraft engine ring (3).
4. The semi-enclosed clamping device for machining an aircraft engine ring according to claim 1, characterized in that: The rotating assembly (5) comprises a rotating shaft (501), a bearing (502) and a rotating disk (503); The rotating shaft (501) is arranged in the middle of the placement plate (2) via the bearing (502), the rotating disk (503) is arranged at the upper end of the rotating shaft (501), and the bottom end surface of the rotating disk (503) is higher than the upper end surface of the placement plate (2).
5. A semi-enclosed clamping device for machining an aircraft engine ring according to claim 4, characterized in that: The semi-enclosed clamping assembly (6) comprises a clamping cylinder (601) and a clamping block (602); The clamping cylinder (601) is arranged on the rotating disk (503), and the clamping block (602) is arranged at the output end of the clamping cylinder (601).
6. A semi-enclosed clamping device for machining an aircraft engine ring according to claim 5, characterized in that: A side surface of the clamping block (602) facing the inner circumference of the aircraft engine ring (3) is an arc-shaped surface adapted to the inner circumference of the aircraft engine ring (3).
7. A semi-enclosed clamping device for machining an aircraft engine ring according to claim 6, characterized in that: A step (301) is provided at the middle and lower part of the inner circumference of the aircraft engine ring (3); a step bayonet (603) is provided on the clamping block (602) at a position corresponding to the step (301) facing the aircraft engine ring (3); and the step bayonet (603) on the clamping block (602) is engaged with the step (301) on the inner circumference of the aircraft engine ring (3).
8. The semi-enclosed clamping device for machining an aircraft engine ring according to claim 7, characterized in that: The upper end surface of the clamping block (602) is flush with one half of the height of the aircraft engine ring (3).