Method for manufacturing a bonding tool

Abstract

The application belongs to the technical field of aero-engine shell assembly processing, and particularly relates to a preparation method of a tool for gluing, which comprises the following steps: a casting base step, a machining allowance layer step, a machining mounting hole step, a machining profile step and a mounting stop block step. The tool base and the machining surface are integrally cast in the present application, and then the machining holes and the profile are arranged on the machining surface. The tool manufacturing cycle can be effectively reduced, the tool life is increased, the tool manufacturing cost is reduced, and the yield is improved.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of engine casing assembly processing, and particularly relates to a preparation method of a bonding tool. BACKGROUND

[0002] Engine casing bonding assemblies are special tooling designed and manufactured to complete the bonding process and component forming. The internal structure, mechanical properties and surface quality of the formed assembly can meet the design requirements, and the appearance size can meet the assembly coordination requirements after slight processing or without any processing. The advantages and disadvantages of the bonding tooling play a decisive role in product quality.

[0003] The aluminum honeycomb bonding tooling is used to bond the casing assembly with an aluminum honeycomb intermediate layer. After the tooling is optimized and compensated according to the deformation of the tooling manufacturing parts, the main process of the original metal aluminum honeycomb bonding tooling manufacturing is as follows: the profile uses 30mm pre-stretching plate material to pass through roll bending, combined welding and stress relief treatment; the support base is laser cut, combined welded, stress relieved, CNC processed; then the support base is combined with the profile, welded, stress relieved, CNC roughly processed, stress relieved, CNC finely processed, deformation compensation processed and shaped; the stop block is CNC processed; the stop block is installed on the tooling profile, and screws, positioning pins and the like are arranged. The existing bonding tooling has the disadvantages of long manufacturing cycle, complex process, high cost, high cost and low yield. SUMMARY

[0004] Therefore, the application provides a preparation method of a bonding tooling, which integrally casts a tooling base and a processing surface, then sets processing holes and processing profiles on the processing surface, so as to effectively reduce the tooling manufacturing cycle, increase the tooling life, reduce the tooling manufacturing cost and improve the yield.

[0005] In order to achieve the above technical purposes, the application adopts the following specific technical scheme:

[0006] A preparation method of a bonding tooling, which is used for bonding and clamping of an engine casing assembly; the engine casing assembly comprises two layers of skins and an aluminum honeycomb casing which are bonded to each other; the aluminum honeycomb casing is arranged between the two layers of skins; the preparation method of the bonding tooling comprises the following steps:

[0007] S101: casting a base, which is provided with a processing surface; and processing a surplus layer on the processing surface;

[0008] S102: processing mounting holes on the surplus layer;

[0009] S103: processing a profile based on the surplus layer; the profile is precisely fitted with the inner concave surface of the skin of the casing assembly;

[0010] S104: installing the stopper on the periphery of the profile based on the mounting hole; the stopper is used to clamp the shell assembly on the profile, and when clamped, the inner concave surface is attached to the profile;

[0011] Wherein: during casting, the processing surface is arranged according to a structure capable of being attached to the inner concave surface of the shell assembly.

[0012] Further, the number of the stoppers is multiple groups, and the multiple groups of stoppers completely wrap the side edge of the shell assembly after being spliced.

[0013] Further, the S102 and the S104 further include the following steps:

[0014] The base and the excess layer are subjected to stress relief treatment.

[0015] Further, the S103 further includes the following steps:

[0016] The casting sand eyes of the profile are blocked based on the high-temperature-resistant sealing glue, and then the profile is scraped flat.

[0017] Further, the high-temperature-resistant sealing glue is DG-3 high-temperature-resistant sealing glue.

[0018] Further, the method for processing the excess layer and the profile is cutting processing.

[0019] Further, the thickness of the excess layer is 10 mm.

[0020] By adopting the technical scheme, the present application can bring the following beneficial effects:

[0021] The gluing tool of the present application can repeatedly perform gluing on the shell assembly, prolonging the service life;

[0022] The base and the processing surface are integrally cast, reducing welding deformation;

[0023] The present application can solve the air leakage problem of sand eyes during casting;

[0024] The present application shortens the manufacturing cost and manufacturing period of the metal aluminum honeycomb gluing tool. BRIEF DESCRIPTION OF DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the following will briefly introduce the drawings needed to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present disclosure, and other drawings can be obtained by those skilled in the art without creative labor.

[0026] Figure 1 Flow chart of a method for preparing a tool for bonding in the specific embodiment of the present application;

[0027] Figure 2 Schematic diagram of the overall structure of a tool for bonding in the specific embodiment of the present application;

[0028] Figure 3 Schematic diagram of the structure of a profile of a tool for bonding in the specific embodiment of the present application;

[0029] Figure 4 Schematic diagram of the state of a tool for bonding after the excess layer is processed in the specific embodiment of the present application;

[0030] Wherein: 1, base; 2, excess layer; 3, mounting hole; 4, profile; 5, stop block. DETAILED DESCRIPTION

[0031] The embodiments of the present application will be described in detail below with reference to the drawings.

[0032] The above and other aspects of the present application will become more apparent by describing in detail the embodiments thereof with reference to the attached drawings in which:

[0033] It is to be understood that the foregoing description is that of certain examples of the application and variations in the specific embodiments can be made to the application without departing from the scope of the application as recited in the appended claims. For example, expected minimum and maximum ranges or amounts, as well as other values, can be combined. It will be apparent to one of ordinary skill in the art that aspects of the application, as described herein, can be implemented in various forms of hardware, software, or both. Furthermore, the described aspects can be implemented alone or in any combination tangible non-transitory or transitory computer readable medium utilizing any set of codes made from any composition of functional instructions. Any of the previously described devices, components, methods, and / or objects can be rearranged and / or combined into their various permutations in accordance with the specific needs of particular applications. The same or equivalent numerical references may

[0034] It is also necessary to note that the drawings provided in the following embodiments only schematically illustrate the basic concepts of the present disclosure, and only the components related to the present disclosure are shown in the drawings, not the number, shape and size of the components when actually implemented, and the shape, number and proportion of each component when actually implemented can be arbitrarily changed, and the component layout pattern can also be more complex.

[0035] In addition, in the following description, specific details are provided in order to facilitate a thorough understanding of the examples. However, one skilled in the art will understand that the aspects described can be practiced without these specific details.

[0036] In one embodiment of the present application, a preparation method of a tool for bonding is provided, and the tool is used for clamping and bonding of an engine shell assembly; the engine shell assembly includes two layers of skin and one layer of aluminum honeycomb shell bonded to each other; the aluminum honeycomb shell is arranged between the two layers of skin; as shown in the drawings, the preparation method of the tool for bonding includes the following steps: Figure 1 The preparation method of the tool for bonding includes the following steps:

[0037] S101: Casting a base 1, the base 1 is provided with a machining surface; a surplus layer 2 is machined on the machining surface (as shown in the drawings) ; Figure 4

[0038] S102: Machining a mounting hole 3 on the surplus layer 2;

[0039] S103: Machining a profile 4 based on the surplus layer 2; the profile 4 is precisely fitted with the inner concave surface skin;

[0040] S104: Installing a stop block 5 on the periphery of the profile 4 based on the mounting hole 3 (as shown in the drawings) ; the stop block 5 is used to clamp the shell assembly on the profile 4, and when clamped, the inner concave surface is fitted with the profile 4; Figure 2 3

[0041] Wherein: during casting, the machining surface is arranged according to the structure capable of being fitted with the inner concave surface skin of the shell assembly.

[0042] In this embodiment, the number of stop blocks 5 is multiple groups, and the multiple groups of stop blocks 5 completely wrap the side edges of the shell assembly after splicing.

[0043] In this embodiment, the steps between S102 and S103 further include the following steps:

[0044] The base 1 and the surplus layer 2 are subjected to stress relief treatment.

[0045] In this embodiment, the steps after S103 further include the following steps:

[0046] The casting sand holes of the profile 4 are blocked based on high-temperature resistant sealant, and then the profile 4 is scraped flat.

[0047] ​​​In the embodiment, the high-temperature-resistant sealing glue is DG-3 high-temperature-resistant sealing glue.

[0048] In the embodiment, the method for processing the excess layer 2 and the profile 4 is cutting.

[0049] In the embodiment, the thickness of the excess layer 2 is 10 mm.

[0050] In the embodiment, the base 1 is hollow, and the precision of the casting process is too low to completely match the inner converging surface of the shell assembly, but the casting part needs to be designed to be able to match the skin of the inner converging surface as much as possible, and the excess layer 2 needs to be considered during casting.

[0051] Meanwhile, the base 1 can be provided with a lifting ring and other devices facilitating transportation.

[0052] In the embodiment, the installation mode of the stop block 5 is that the stop block 5 at the corresponding position is positioned based on the positioning pin cooperating with the bushing, and then the stop block 5 is fixed on the processed surface by using the screw cooperating with the bushing. The bushing is arranged in the mounting hole 3, and is used to reduce the wear of the hole.

[0053] In the embodiment, the base 1 is integrally cast by using ZL105A, the profile 4 is coarsely processed by using three-axis numerical control milling, after stress relief treatment, the profile 4 of the base 1 is processed by using five-axis numerical control milling, the sand holes of the profile 4 are blocked by using DG-3 high-temperature-resistant glue, and are scraped flat; the stop block 5 is processed by using five-axis milling by using 7075 pre-stretching material; and the base 1 and the stop block 5 are assembled together, and after passing the inspection, the tooling is completed.

[0054] The above merely describes the specific embodiments of the present disclosure, but the protection scope of the present disclosure is not limited thereto, and any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present disclosure, which should be covered within the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be subject to the protection scope of the claims.

Claims

1. A method of producing a jig for use in cementing, characterized by, The tool is used for clamping of the engine shell assembly by gluing; the engine shell assembly comprises two layers of skin and one layer of aluminum honeycomb shell which are glued to each other; The aluminum honeycomb shell is arranged between the two layers of the skin; the preparation method of the tool for gluing comprises the following steps: S101: casting a base, a machining surface is arranged on the base; a surplus layer is machined on the machining surface; S102: installing a mounting hole on the surplus layer; S103: machining a profile surface based on the surplus layer; the profile surface is precisely fitted with the inner recess surface skin of the shell assembly; S104: installing a stopper on the periphery of the profile surface based on the mounting hole; the stopper is used for clamping the shell assembly on the profile surface, and when clamped, the inner recess surface skin is fitted with the profile surface; Wherein: during casting, the machining surface is arranged according to the structure which can be fitted with the inner recess surface skin of the shell assembly.

2. The method of claim 1, wherein The number of the stoppers is multiple groups, and multiple groups of the stoppers are spliced to completely wrap the side edge of the shell assembly.

3. The method of claim 1, wherein The steps between S102 and S103 further comprise: Stress relief treatment is performed on the base and the surplus layer.

4. The method of claim 1, wherein The steps after S103 further comprise: High-temperature-resistant sealing glue is used to seal the casting sand eyes of the profile surface, and then the profile surface is scraped flat.

5. The method of claim 4, wherein The high-temperature-resistant sealing glue is DG-3 high-temperature-resistant sealing glue.

6. The method of claim 1, wherein The method for machining the surplus layer and the profile surface is cutting.

7. The method of claim 1, wherein The thickness of the surplus layer is 10mm.

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