Machining tool and method for butt joint shaft of ceramic matrix composite airfoil product component

Abstract

The invention provides a machining tool and method for a butt joint shaft of a ceramic matrix composite airfoil product component. The machining tool and method are used for solving the technical problem that the precision of the butt joint shaft of an existing airfoil product component cannot meet the design requirement. The machining tool comprises a base, a supporting unit and a tensioning assembly. The base is of a rectangular plate-shaped structure, the supporting unit comprises two supporting assemblies which are symmetrically arranged in the length direction of the base, and a gap exists between the two supporting assemblies; each supporting assembly comprises a plurality of supporting seats, each supporting seat is vertically installed on the base, and the upper end faces of all the supporting seats jointly form a curved surface which is the same as the upper end face of a to-be-machined airfoil product component skeleton structure; the tensioning assembly comprises a plurality of braces; the two ends of each brace are connected with the tops of the two corresponding supporting bases in the two supporting assemblies correspondingly and used for fixing the two corresponding supporting bases correspondingly. The airfoil product component obtained based on the machining tool is high in butt joint shaft precision.

Description

Technical Field

[0001] The invention relates to a method for processing a reference shaft, and in particular to a processing tool and method for a butt joint shaft of a wing surface product component made of ceramic matrix composite material. Background Art

[0002] Ceramic-based composites are a new type of strategic material that combines the performance advantages of metal materials, ceramic materials and carbon materials. Due to the limitations of the molding process, it is difficult to achieve the overall preparation of large-scale, high-precision composite components of this type of material. Therefore, finished parts based on this type of material are usually prepared by small-size parts and then manufactured by online integrated assembly.

[0003] For ceramic matrix composite wing surface components, there are 2-5 docking shafts on the skeleton structure. During the assembly process of the product, the above docking shafts are used as the installation reference, and the other skeleton parts are assembled and connected by pins and bolts according to the assembly requirements. After the skeleton assembly is completed, the skin is installed by pins and screws. Therefore, the processing quality and precision of the docking shaft as the installation reference are particularly important.

[0004] In the existing ceramic-based composite wing surface product components, the skeleton structure is made of ceramic-based composite materials, while the docking shaft is made of metal. The processing method is to process the two separately, and then assemble the two into one by bolts after the processing is completed. However, during the assembly process, due to factors such as assembly accuracy, clearance elimination, and bolt tightening force, it is easy to cause deviations in the installation of the docking shaft, and the installation accuracy cannot meet the design requirements. In addition, after the assembly is completed, due to the influence of the stress of the pins and bolts inside the components, it is easy to cause high-temperature deformation of the components during high-temperature deposition treatment, thereby affecting the subsequent assembly docking accuracy of the metal shaft and the accuracy of the wing surface docking position. Summary of the invention

[0005] The purpose of the present invention is to solve the technical problem that the precision of the butt joint shaft of the wing surface product component obtained by the existing processing method cannot meet the design requirements, and to provide a processing tool and method for the butt joint shaft of the wing surface product component of a ceramic matrix composite material.

[0006] To achieve the above objectives, the technical solutions provided by the present invention are:

[0007] A processing tool for a butt joint shaft of a ceramic matrix composite material wing surface product component, which is special in that it includes a base, a support unit and a tensioning assembly;

[0008] The base is a rectangular plate-shaped structure, and the support unit includes two groups of support components symmetrically arranged along the axis of the length direction of the base, and there is a gap between the two groups of support components for accommodating the skeleton structure of the wing surface product component to be processed;

[0009] Each support assembly includes a plurality of support seats arranged along the length direction of the base, each support seat is vertically mounted on the base, and the upper end surfaces of all the support seats together form a curved surface consistent with the upper end surface of the skeleton structure of the wing surface product component to be processed;

[0010] The tensioning assembly includes multiple tie rods; the two ends of each tie rod are respectively connected to the tops of two corresponding support seats in the two groups of support assemblies, and are respectively used to fix the two corresponding support seats, and the docking axis of the wing surface product component to be processed is located between two adjacent tie rods.

[0011] Further, the support unit further comprises a first bottom support located between the two groups of support assemblies;

[0012] The bottom of the first bottom support is installed on the base, and the top is an inclined surface adapted to the lower end surface of the skeleton structure of the wing surface product component to be processed, and is used to support the inclined surface part of the lower end surface of the skeleton structure.

[0013] Furthermore, the base is also provided with a baffle for supporting one end face of the skeleton structure of the wing surface product component to be processed in the length direction.

[0014] Furthermore, the support unit also includes a second bottom support, which is arranged close to the baffle and installed on the base, and is located between the first bottom support and the baffle, and is used to support the horizontal part of the lower end surface of the skeleton structure of the wing surface product component to be processed.

[0015] Furthermore, each of the support seats is provided with one or more protrusions on the inner side surface, and an accommodating space is formed between all the protrusions of the two groups of support assemblies away from one end of the support seat where they are located, and the virtual surfaces formed by the protrusions on both sides of the accommodating space are consistent with the outer shapes of the two side surfaces of the skeleton structure of the wing surface product component to be processed.

[0016] Furthermore, lifting rings are respectively provided at the four corners of the base.

[0017] At the same time, the present invention also provides a method for processing a butt joint shaft of a ceramic matrix composite wing surface product component, comprising the following steps:

[0018] Step [1], processing according to the process requirements to obtain a semi-finished airfoil product component, wherein the airfoil product component includes a skeleton structure and a plurality of docking shafts vertically arranged on the same side of the skeleton structure; the docking shafts have a circumferential margin of 0.5 to 1 mm;

[0019] Step [2], assembling the processing tooling for the docking shaft of the ceramic-based composite material wing surface product component of the present invention, vertically placing the skeleton structure of the semi-finished wing surface product component between the two groups of support components, and connecting the tops of the two corresponding support seats with tie rods, so that each docking shaft is located between two adjacent tie rods;

[0020] Step [3]: Use a CNC milling machine to finish-process each docking shaft in turn to remove excess;

[0021] Step [4], removing the wing surface product component processed in step [3] from the processing tooling, thereby completing the processing of the ceramic matrix composite material wing surface product component docking shaft.

[0022] Furthermore, step [2] is specifically as follows:

[0023] 2.1. Complete the assembly of each support seat, the first bottom support, the second bottom support, the baffle and the base in the two groups of support assemblies according to the shape of the semi-finished skeleton structure of the wing product component;

[0024] 2.2. Place the skeleton structure of the semi-finished wing product component vertically between two groups of support assemblies, so that the side of the skeleton structure with the docking axis faces upward, and the side of the skeleton structure away from the docking axis is defined as its lower end face, then the inclined portion of the lower end face contacts the top of the first bottom support, the horizontal portion contacts the top of the second bottom support, and the end away from the inclined portion in the length direction contacts the side of the baffle close to the second bottom support; at the same time, one side surface of the skeleton structure contacts the protrusion of each support seat in one group of support assemblies, and a gap is left between the other side surface and the protrusion of each support seat in the other group of support assemblies;

[0025] 2.3. Use bolts to connect each support seat in the other group of support assemblies to the other side of the skeleton structure, and use tie rods to connect the tops of the two corresponding support seats in the two groups of support assemblies, so that each docking axis is located between two adjacent tie rods.

[0026] Furthermore, in step [3], during the fine processing, the pull rod on the side of the docking shaft to be processed needs to be removed and processed step by step. After the processing of one side is completed, the pull rod on that side is installed.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. The processing tooling for the docking shaft of the ceramic-based composite material wing surface product component provided by the present invention comprises a base, a support unit and a tensioning assembly, wherein the support unit comprises two groups of support assemblies arranged symmetrically for accommodating the skeleton structure of the wing surface product component to be processed, each group of support assemblies comprises a plurality of support seats, and the tops thereof are fastened and connected by tie rods. The overall structure is simple, and the wing surface product component to be processed can be quickly and stably fixed, thereby realizing high-precision processing of the docking shaft.

[0029] 2. The processing tooling for the ceramic-based composite material wing surface product component docking shaft provided by the present invention is also provided with a first bottom support, a second bottom support and a baffle on the base, thereby improving the stability of the support and further improving the processing accuracy.

[0030] 3. The processing tooling for the docking shaft of the ceramic-based composite wing surface product component provided by the present invention provides one or more protrusions on the inner side surface of each support seat, thereby avoiding damage to the surface of the skeleton structure caused by excessive contact between the support seat and the skeleton structure during processing.

[0031] 4. The processing tooling for the butt joint shaft of the ceramic matrix composite material wing surface product component provided by the present invention is simple to assemble and accurately positioned, thereby ensuring that the precision of the butt joint shaft meets the design requirements.

[0032] 5. The method for processing the butt joint shaft of the ceramic-based composite material wing surface product component provided by the present invention has a simple processing mode, is easy to operate, and has high processing efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a schematic diagram of the structure of the wing product components.

[0034] Figure 2 The present invention is a schematic structural diagram of an embodiment of a processing tooling for a butt joint shaft of a ceramic-based composite wing surface product component.

[0035] Figure 3 It is a structural schematic diagram of a base in an embodiment of a processing tooling for a butt joint shaft of a ceramic-based composite wing surface product component of the present invention.

[0036] Figure 4 The present invention is a schematic structural diagram of a group of supporting components in a processing tooling embodiment of a ceramic-based composite material wing surface product component docking shaft.

[0037] Figure 5 The present invention is a schematic diagram of the assembly structure of a processing tool for a butt joint shaft of a ceramic-based composite material wing surface product component and a wing surface product component to be processed.

[0038] The reference numerals are as follows:

[0039] 1-base, 11-lifting ring, 2-support seat, 21-protrusion, 3-pull bar, 4-first bottom support, 5-baffle, 6-second bottom support, 7-skeleton structure, 8-docking shaft. DETAILED DESCRIPTION

[0040] In order to make the purpose, advantages and features of the present invention clearer, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood by those skilled in the art that these embodiments are only used to explain the technical principles of the present invention and are not intended to limit the scope of protection of the present invention.

[0041] like Figure 2 As shown, this embodiment provides a processing tool for a ceramic matrix composite wing surface product component butt joint shaft, including a base 1, a support unit and a tensioning assembly. In order to avoid the influence of external factors on the precision of the wing surface product component during the assembly process, such as Figure 1 As shown, in this embodiment, the component is designed as a structure in which the skeleton structure 7 and the docking shaft 8 are integrated, so as to improve the overall processing accuracy and subsequent assembly accuracy.

[0042] Combination Figure 1 and Figure 3 As shown, the base 1 is a rectangular plate-like structure, and the support unit includes two groups of support components symmetrically arranged along the axis of the length direction of the base 1. There is a gap between the two groups of support components for accommodating the skeleton structure of the wing surface product component to be processed.

[0043] Each group of support components includes a plurality of support seats 2 arranged along the length direction of the base 1, each support seat 2 is vertically mounted on the base 1, and the upper end surfaces of all support seats 2 together form a curved surface consistent with the upper end surface shape of the skeleton structure 7 of the wing surface product component to be processed.

[0044] The tensioning assembly includes multiple pull rods 3; the two ends of each pull rod 3 are respectively connected to the tops of two corresponding support seats 2 in the two groups of support assemblies, and are respectively used to fix the two corresponding support seats 2, and make the docking axis 8 of the wing surface product component to be processed be located between two adjacent pull rods 3.

[0045] In order to provide support stability, the support unit also includes a first bottom support 4 and a second bottom support 6 located between the two groups of support components and respectively mounted on the base 1. Since one end of the skeleton structure 7 of the wing surface product component to be processed away from the docking axis 8 is an inclined structure, and the other end is a horizontal structure, therefore, in this embodiment, the top of the first bottom support 4 is designed as an inclined surface that matches the lower end surface of the skeleton structure 7 of the wing surface product component to be processed (i.e., the side away from the docking axis 8), which is used to support the inclined surface portion of the lower end surface of the skeleton structure 7, while the second bottom support 6 is used to support the horizontal portion of the lower end surface of the skeleton structure 7 of the wing surface product component to be processed.

[0046] At the same time, in this embodiment, a baffle 5 is provided on the base 1 for supporting one end face of the skeleton structure 7 of the wing surface product component to be processed in the length direction, so as to improve the stability of the wing surface product component to be processed during processing.

[0047] like Figure 4 As shown, in order to avoid damaging the surface of the wing product component to be processed, the present embodiment further provides one or more protrusions 21 on the inner side surface of each support seat 2, and all the protrusions 21 of the two groups of support assemblies form a accommodating space away from one end of the support seat 2 where they are located, and the virtual surfaces formed by the protrusions 21 on both sides of the accommodating space are consistent with the outer shapes of the two side surfaces of the skeleton structure of the wing product component to be processed.

[0048] Lifting rings 11 are respectively provided at the four corners of the base 1 to facilitate the movement and transportation of the entire tooling.

[0049] In addition, the present invention also provides a processing method using the above-mentioned ceramic matrix composite material wing surface product component butt-jointing shaft processing tooling, comprising the following steps:

[0050] Step [1], processing according to the process requirements to obtain a semi-finished airfoil product component, wherein the airfoil product component includes a skeleton structure 7 and a plurality of docking shafts 8 vertically arranged on the same side of the skeleton structure 7; at this time, the skeleton structure has been added to the finished product size, and a 0.5-1 mm margin is left on the circumference of the docking shaft 8.

[0051] Step [2]: assemble the processing tooling of the above-mentioned ceramic matrix composite wing surface product component docking shaft, and vertically place the skeleton structure 7 of the semi-finished wing surface product component between the two groups of support components, specifically:

[0052] 2.1. According to the shape of the semi-finished skeleton structure 7 of the wing product component, complete the assembly of each support seat 2, the first bottom support 4, the second bottom support 6, and the baffle 5 with the base 1 in the two groups of support components. Among them, the height of the support seat 2 is matched and designed according to the width of the skeleton structure 7, the number of the support seats 2 is determined according to the number of docking shafts 8, generally every 4 support seats 2 correspond to one docking shaft 8, and the number of the braces 3 is determined according to the number of the support seats 2.

[0053] 2.2. Place the semi-finished skeleton structure 7 of the wing product component vertically between the two groups of support components, so that the side of the skeleton structure 7 with the docking axis 8 faces upward, and this side is defined as the upper end face of the skeleton structure 7, and the side away from the docking axis 8 of the skeleton structure 7 is its lower end face. The inclined portion of the lower end face contacts the top of the first bottom support 4, the horizontal portion contacts the top of the second bottom support 6, and the end in the length direction away from the inclined portion contacts the side of the baffle 5 close to the second bottom support 6.

[0054] At the same time, one side surface of the skeleton structure 7 in the thickness direction contacts the protrusion 21 of each support seat 2 in one group of support components, and a gap is left between the other side surface and the protrusion 21 of each support seat 2 in the other group of support components.

[0055] 2.3. Use bolts to connect each support seat 2 in the other support assembly to the other side of the skeleton structure 7, and use tie bars 3 to connect the tops of the two corresponding support seats 2 in the two support assemblies, so that each docking shaft 8 is located between two adjacent tie bars 3, as shown in FIG. Figure 5 shown.

[0056] Step [3]: Use a CNC milling machine to perform fine processing on each docking shaft 8 in turn to remove the excess. During fine processing, in order to ensure the processing accuracy, it is necessary to remove the pull rod 3 close to the side of the docking shaft 8 to be processed, and process it step by step. After the processing of one side is completed, the pull rod 3 on that side is installed. All docking shafts 8 are finely processed according to this processing method.

[0057] Step [4], removing the wing surface product component processed in step [3] from the processing tooling, thereby completing the processing of the ceramic matrix composite material wing surface product component docking shaft.

[0058] The processing accuracy of the docking shaft obtained by the processing method of this embodiment is relatively high, thereby ensuring the installation reference of the wing surface product component and other components, thereby improving the assembly accuracy and quality of the product.

[0059] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present invention.

Claims

1. A processing tool for the butt joint shaft of a ceramic matrix composite wing product component, characterized in that: It comprises a base (1), a support unit and a tensioning assembly; The base (1) is a rectangular plate-shaped structure, and the support unit comprises two groups of support components symmetrically arranged along the axis of the length direction of the base (1), and there is a gap between the two groups of support components for accommodating the skeleton structure of the wing surface product component to be processed; Each group of support assemblies comprises a plurality of support seats (2) arranged along the length direction of the base (1), each support seat (2) is vertically mounted on the base (1), and the upper end surfaces of all the support seats (2) together form a curved surface consistent with the upper end surface of the skeleton structure of the wing surface product component to be processed; The tensioning assembly comprises a plurality of tie rods (3); the two ends of each tie rod (3) are respectively connected to the tops of two corresponding support seats (2) in the two groups of support assemblies, and are respectively used to fix the two corresponding support seats (2), and the docking axis of the wing surface product component to be processed is located between two adjacent tie rods (3).

2. The processing tooling for the butt joint shaft of a ceramic matrix composite wing surface product component according to claim 1 is characterized in that: The support unit further comprises a first bottom support (4) located between the two groups of support components; The bottom of the first bottom support (4) is mounted on the base (1), and the top is an inclined surface adapted to the lower end surface of the skeleton structure of the wing surface product component to be processed, and is used to support the inclined surface portion of the lower end surface of the skeleton structure.

3. The processing tooling for the butt joint shaft of the ceramic matrix composite wing surface product component according to claim 2 is characterized by: The base (1) is also provided with a baffle (5) for supporting an end face in the length direction of the skeleton structure of the wing surface product component to be processed.

4. The processing tooling for the butt joint shaft of a ceramic matrix composite wing surface product component according to claim 3 is characterized by: The support unit further comprises a second bottom support (6), which is arranged close to the baffle (5) and mounted on the base (1), and is located between the first bottom support (4) and the baffle (5), and is used to support the horizontal part of the lower end surface of the skeleton structure of the wing surface product component to be processed.

5. The processing tool for the butt joint shaft of a ceramic matrix composite wing surface product component according to any one of claims 1 to 4, characterized in that: The inner side surface of each support seat (2) is respectively provided with one or more protrusions (21), and a receiving space is formed between all the protrusions (21) of the two groups of support assemblies away from one end of the support seat (2) where they are located, and the virtual surfaces formed by the protrusions (21) on both sides of the receiving space are consistent with the outer shapes of the two side surfaces of the skeleton structure of the wing surface product component to be processed.

6. The processing tooling for the butt joint shaft of a ceramic matrix composite wing surface product component according to claim 1 is characterized by: The base (1) is provided with lifting rings (11) at the four corners.

7. A method for processing a butt joint shaft of a ceramic matrix composite wing product component, characterized in that: The following steps are involved: Step [1], processing in accordance with the process requirements to obtain a semi-finished wing surface product component, wherein the wing surface product component comprises a skeleton structure (7) and a plurality of docking shafts (8) vertically arranged on the same side of the skeleton structure (7); a circumferential margin of 0.5 to 1 mm is left on the docking shafts (8); Step [2], assembling the processing tooling for the butt joint shaft of the ceramic-based composite wing surface product component according to any one of claims 1 to 5, vertically placing the skeleton structure (7) of the semi-finished wing surface product component between two groups of support components, and connecting the tops of the corresponding two support seats (2) with tie rods (3), so that each butt joint shaft (8) is located between two adjacent tie rods (3); Step [3], using a CNC milling machine to perform fine processing on each docking shaft (8) in turn to remove excess; Step [4], removing the wing surface product component processed in step [3] from the processing tooling, thereby completing the processing of the ceramic matrix composite material wing surface product component docking shaft.

8. The method for processing the butt joint shaft of a ceramic matrix composite wing surface product component according to claim 7, characterized in that: Step [2] is as follows: 2.

1. According to the shape of the semi-finished skeleton structure (7) of the wing surface product component, complete the assembly of each support seat (2), the first bottom support (4), the second bottom support (6) and the baffle (5) with the base (1) in the two groups of support assemblies; 2.

2. The skeleton structure (7) of the semi-finished wing surface component is placed vertically between two groups of support components, so that the side of the skeleton structure (7) provided with the docking axis (8) faces upward, and the side of the skeleton structure (7) away from the docking axis (8) is defined as its lower end face, then the inclined portion of the lower end face contacts the top of the first bottom support (4), the horizontal portion contacts the top of the second bottom support (6), and the end away from the inclined portion in the length direction contacts the side of the baffle (5) close to the second bottom support (6); at the same time, one side surface of the skeleton structure (7) contacts the protrusion (21) of each support seat (2) in one group of support components, and a gap is left between the other side surface and the protrusion (21) of each support seat (2) in the other group of support components; 2.

3. Use bolts to connect each support seat (2) in the other group of support components to the other side of the skeleton structure (7), and use tie bars (3) to connect the tops of the two corresponding support seats (2) in the two groups of support components, so that each docking shaft (8) is located between two adjacent tie bars (3).

9. The method for processing the butt joint shaft of a ceramic matrix composite wing surface product component according to claim 7 or 8, characterized in that: In step [3], during the fine processing, the pull rod (3) on the side to be processed close to the docking shaft (8) needs to be removed and processed step by step. After the processing on one side is completed, the pull rod (3) on that side is installed.

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