Aero-engine exhaust nozzle cross beam machining clamp

Abstract

The utility model discloses an aero-engine exhaust nozzle cross beam machining clamp which comprises a base, and a first centering clamp and a second centering clamp are arranged at the two ends of the base in the length direction respectively. The upper end face of the first centering clamp is higher than the upper end face of the second centering clamp and makes contact with the lower top face of the exhaust nozzle cross beam. A supporting pedestal is arranged on the side, close to the second centering clamp, between the first centering clamp and the second centering clamp, a pressing plate attached to the hollow bottom of the exhaust nozzle cross beam is arranged between the supporting pedestal and the first centering clamp, a fastening screw is connected to the pressing plate in a penetrating mode from top to bottom, and a first threaded hole matched with the fastening screw is formed in the base. The clamp has the advantages of being reasonable in design, accurate in positioning, firm in clamping, good in supporting performance for machining sites, small in machining deformation and high in precision.

Description

Technical Field

[0001] This utility model relates to a parts processing fixture, and more particularly to a machining fixture for the crossbeam of an aero-engine tail nozzle. Background Technology

[0002] A schematic diagram of the general structure of the tail nozzle crossbeam of an aircraft engine is attached to the instruction manual. Figure 6 As shown, the front view resembles a small boat. When machining the blank of the aircraft engine exhaust nozzle crossbeam, the main steps required are as shown in the attached instruction manual. Figure 5 The holes a, b, c and d shown are machined, and the bosses also need to be milled. These machining operations are generally performed in a machining center.

[0003] To facilitate machining and ensure the machining accuracy of parts, the blanks of aero-engine exhaust nozzle crossbeams often need to be fixed in special fixtures. However, since aero-engine exhaust nozzle crossbeams are irregularly shaped parts with many machining surfaces, and the material of the machining surfaces is generally thin, their clamping, fixing, and anti-deformation support pose considerable challenges to the machining process.

[0004] The main technical problem in the current machining of aero-engine tail nozzle crossbeam blanks is the unreasonable design of the fixing fixture, which leads to inaccurate positioning, low clamping firmness, poor support, and the possibility of deformation, resulting in low machining accuracy. Utility Model Content

[0005] To address the aforementioned technical problems, this utility model provides a machining fixture for the crossbeam of an aero-engine exhaust nozzle. This utility model features a reasonable design, precise positioning, secure clamping, good support for the machining site, minimal machining deformation, and high precision.

[0006] The technical solution of this utility model:

[0007] A machining fixture for an aero-engine tail nozzle crossbeam includes a base, with a first centering clamp and a second centering clamp respectively provided at both ends of the base along its length; the upper end face of the first centering clamp is higher than the upper end face of the second centering clamp and contacts the lower top surface of the tail nozzle crossbeam.

[0008] A support platform is provided between the first split clamp and the second split clamp, near the second split clamp. A pressure plate is provided between the support platform and the first split clamp, which fits against the bottom of the inner cavity of the tail nozzle crossbeam. A fastening screw is connected through the pressure plate from top to bottom. A first threaded hole that mates with the fastening screw is provided on the base.

[0009] This solution uses the second center clamp as the positioning point in the length direction, the support base, the first center clamp, and the pressure plate as the longitudinal fixing points, and the first and second center clamps as the lateral fastening and positioning points. The overall design is reasonable, with higher positioning accuracy and more secure clamping.

[0010] Preferably, in the aforementioned machining fixture for the tailpipe crossbeam of an aero-engine, the first centering clamp is provided with two support columns on the outer side of the second centering clamp, and the two support columns are symmetrically arranged on both sides of the base length direction.

[0011] This solution improves the support effect, reduces processing deformation, and achieves higher precision by setting two support columns to support the machining points at the end of the tail nozzle crossbeam.

[0012] Preferably, in the aforementioned machining fixture for the tail nozzle crossbeam of an aero-engine, the lower section of the first support column is a threaded column, and the base is provided with a second threaded hole that mates with the first support column.

[0013] The support column of this solution is connected to the base by a thread, and its height is adjustable, making it more flexible, more rationally designed, and more convenient to use.

[0014] Preferably, in the aforementioned machining fixture for the tail nozzle crossbeam of an aero-engine, the top of the support column one is provided with a recessed hole.

[0015] This design, by setting a recessed hole at the top of the support column, facilitates drilling at the support point and is more rationally designed.

[0016] Preferably, in the aforementioned aero-engine tail nozzle crossbeam machining fixture, two support columns are provided between the support base and the pressure plate, and the two support columns are symmetrically arranged on both sides of the base length direction.

[0017] This solution improves the support effect, reduces processing deformation, and achieves higher precision by setting two support columns to support the machining points at the end of the tail nozzle crossbeam.

[0018] Preferably, in the aforementioned machining fixture for the tail nozzle crossbeam of an aero-engine, the lower section of the second support column is a threaded column, and the base is provided with a third threaded hole that mates with the second support column.

[0019] The second support column of this solution is connected to the base by a thread, and its height is adjustable, making it more flexible, more rationally designed, and more convenient to use.

[0020] Preferably, in the aforementioned aero-engine tail nozzle crossbeam machining fixture, two support columns are provided between the first centering clamp and the pressure plate, and the two support columns are symmetrically arranged on both sides of the base length direction.

[0021] This solution improves the support effect, reduces processing deformation, and increases precision by setting two support columns to support the machining points at the end of the tail nozzle crossbeam.

[0022] Preferably, in the aforementioned machining fixture for the tail nozzle crossbeam of an aero-engine, the lower section of the support column three is a threaded column, and the base is provided with a fourth threaded hole that mates with the support column three.

[0023] The support columns in this design are connected to the base via threads, allowing for height adjustment, greater flexibility, a more rational design, and easier use.

[0024] The beneficial effects of this utility model are:

[0025] 1. This utility model uses the second center clamp as the positioning point in the length direction, the support base, the first center clamp and the pressure plate as the longitudinal fixing points, and the first center clamp and the second center clamp as the lateral fastening and positioning points. The overall design is reasonable, the positioning accuracy is higher, and the clamping is more secure.

[0026] 2. This utility model improves the support effect, reduces processing deformation, and increases precision by setting support columns one, two, and three to support the processing points at the end of the tail nozzle crossbeam.

[0027] 3. The support column one, support column two and support column three of this utility model are all connected to the base by threads, which makes the height adjustable, more flexible, more reasonable in design and more convenient to use.

[0028] 4. This utility model makes it easier to drill holes at the support points by setting a sinkhole at the top of the support column, and the design is more reasonable.

[0029] In summary, this utility model has the advantages of reasonable design, accurate positioning, firm clamping, good support for the processing point, small processing deformation, and high precision. Attached Figure Description

[0030] Appendix Figure 1 This is a three-dimensional structural diagram of the present invention;

[0031] Appendix Figure 2 This is a partial three-dimensional structural schematic diagram of the present invention;

[0032] Appendix Figure 3 For the appendix Figure 1 The main view;

[0033] Appendix Figure 4 This is a partial sectional view of the tail nozzle crossbeam after fixing the present invention.

[0034] Appendix Figure 5 This is the front view of the present invention after fixing the tail nozzle crossbeam;

[0035] Appendix Figure 6 This is a front view of the tail nozzle crossbeam described in this utility model.

[0036] Explanation of reference numerals in the attached drawings: 1-base, 2-first split clamp, 3-second split clamp, 4-support base, 5-pressure plate, 6-fastening screw, 7-first threaded hole, 8-support column one, 9-second threaded hole, 10-support column two, 11-third threaded hole, 12-support column three, 13-fourth threaded hole, 14-sunken hole, 15-tail nozzle crossbeam. Detailed Implementation

[0037] The present invention will be further described below with reference to the embodiments, but this should not be construed as limiting the present invention.

[0038] Embodiments of this utility model

[0039] A machining fixture for the crossbeam of an aircraft engine exhaust nozzle, as shown in the attached document. Figure 1-4 As shown, it includes a base 1, and a first centering clamp 2 and a second centering clamp 3 are respectively provided at both ends of the base 1 along its length. The center lines of the first centering clamp 2 and the second centering clamp 3 coincide. The upper end surface of the first centering clamp 2 is higher than the upper end surface of the second centering clamp 3 and contacts the lower top surface of the tail nozzle crossbeam.

[0040] A support base 4 is provided between the first split clamp 2 and the second split clamp 3 on the side near the second split clamp 3. A pressure plate 5 is provided between the support base 4 and the first split clamp 2, which fits against the bottom of the inner cavity of the tail nozzle crossbeam. A fastening screw 6 is connected through the pressure plate 5 from top to bottom. A first threaded hole 7 that mates with the fastening screw 6 is provided on the base 1.

[0041] In this embodiment, when fixing the crossbeam 15 of the aircraft engine tail nozzle, firstly, the first split clamp 2 and the second split clamp 3 are separated outwards, as shown in the attached diagram. Figure 5 The F-side shown is in close contact with the right side of the second centering clamp 3. The B-side and E-side are pressed onto the first centering clamp 2 and the support base 4, respectively. Then, the adjusting screws of the first centering clamp 2 and the second centering clamp 3 are rotated to clamp the tail nozzle crossbeam. During the clamping process, the tail nozzle crossbeam is prevented from moving to the right. Finally, the pressure plate 5 is pressed into the hollow bottom of the tail nozzle crossbeam, and the fastening screw 6 is screwed into the first threaded hole 7 and tightened to completely fix and position the tail nozzle crossbeam.

[0042] Further implementation, for example, is attached. Figure 1-4 As shown, the first split clamp 2 has two support columns 8 on its outer side relative to the second split clamp 3, and the two support columns 8 are symmetrically arranged on both sides of the base 1 along its length. (See attached diagram) Figure 5 As shown, support column 8 rests on surface A of the tail nozzle crossbeam. Surface A is exactly the area of ​​drill hole a. Supporting it can prevent deformation.

[0043] Further implementation, for example, is attached. Figure 1-4 As shown, the lower section of the support column 8 is a threaded column, and the base 1 is provided with a second threaded hole 9 that mates with the support column 8. When the surface of the tail nozzle crossbeam 15A is uneven, causing the support height to change, the support column 8 can be rotated to adjust it to meet the support requirements.

[0044] Further implementation, for example, is attached. Figure 1-4 As shown, the top of the support column 8 is provided with a recessed hole 14. The diameter of the recessed hole 14 is larger than the diameter of the drill hole a. At this time, even if the end of the drill bit exceeds the lower end face of the drill hole a, it will not cause damage to the support column 8.

[0045] Further implementation, for example, is attached. Figure 1-4 As shown, two support columns 10 are provided between the support base 4 and the pressure plate 5, and the two support columns 10 are symmetrically arranged on both sides of the base 1 along its length. The support points of the support columns 10 are attached. Figure 5 As shown on surface D, the left side of this position is the machining point for borehole c. The strength near borehole c is enhanced by the support of support column 2 10 to prevent deformation.

[0046] Further implementation, for example, is attached. Figure 1-4 As shown, the lower section of the second support column 10 is a threaded column, and the base 1 is provided with a third threaded hole 11 that mates with the second support column 10. Similarly, when the surface of surface D is uneven, causing the support height to change, the support height can be adjusted by rotating the second support column 10.

[0047] Further implementation, for example, is attached. Figure 1-4 As shown, two support columns 12 are provided between the first dividing clamp 2 and the pressure plate 5, and the two support columns 12 are symmetrically arranged on both sides of the base 1 along its length. The support points of the support columns 12 are attached. Figure 5 As shown on surface C, the right side of this position is the machining point for borehole b. The strength near borehole b is enhanced by the support of support column 312 to prevent deformation.

[0048] Further implementation, for example, is attached. Figure 1-4 As shown, the lower section of the support column 12 is a threaded column, and the base 1 is provided with a fourth threaded hole 13 that mates with the support column 12. Similarly, when the surface of surface C is uneven, causing the support height to change, the support height can be adjusted by rotating the support column 12.

[0049] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. An aircraft engine exhaust nozzle beam machining fixture, characterized by: It includes a base (1), and a first split clamp (2) and a second split clamp (3) are respectively provided at both ends of the base (1) along its length; the upper end surface of the first split clamp (2) is higher than the upper end surface of the second split clamp (3) and contacts the lower top surface of the tail nozzle crossbeam. A support base (4) is provided between the first split clamp (2) and the second split clamp (3) on the side near the second split clamp (3). A pressure plate (5) is provided between the support base (4) and the first split clamp (2) to fit the bottom of the inner cavity of the tail nozzle crossbeam. A fastening screw (6) is connected through the pressure plate (5) from top to bottom. A first threaded hole (7) that mates with the fastening screw (6) is provided on the base (1).

2. The jet engine exhaust nozzle beam machining fixture of claim 1, wherein: The first split clamp (2) is provided with two support columns (8) on the outer side of the second split clamp (3), and the two support columns (8) are symmetrically arranged on both sides of the base (1) in the length direction.

3. The aircraft engine exhaust nozzle beam machining fixture of claim 2, wherein: The lower section of the support column (8) is a threaded column, and the base (1) is provided with a second threaded hole (9) that mates with the support column (8).

4. The aircraft engine exhaust nozzle beam machining fixture of claim 2, wherein: The top of the support column (8) is provided with a recessed hole (14).

5. The jet engine exhaust nozzle beam machining fixture of claim 1, wherein: Two support columns (10) are provided between the support base (4) and the pressure plate (5), and the two support columns (10) are symmetrically arranged on both sides of the base (1) along its length.

6. The aircraft engine exhaust nozzle beam machining fixture of claim 5, wherein: The lower section of the second support column (10) is a threaded column, and the base (1) is provided with a third threaded hole (11) that mates with the second support column (10).

7. The jet engine exhaust nozzle beam machining fixture of claim 1, wherein: Two support columns (12) are provided between the first split clamp (2) and the pressure plate (5), and the two support columns (12) are symmetrically arranged on both sides of the base (1) in the length direction.

8. The machining fixture for the tail nozzle crossbeam of an aero-engine according to claim 7, characterized in that: The lower section of the support column three (12) is a threaded column, and the base (1) is provided with a fourth threaded hole (13) that mates with the support column three (12).

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