Processing tool and method for ceramic matrix composite airfoil product member butt joint shaft

Abstract

The application provides a processing tool and method for a ceramic matrix composite airfoil product component butt joint shaft, and aims at solving the technical problem that the precision of the existing airfoil product component butt joint shaft cannot meet the design requirements. The processing tool comprises a base, a supporting unit and a tensioning assembly. The base is in a rectangular plate structure. The supporting unit comprises two groups of supporting assemblies which are symmetrically arranged along the length direction of the base, and there is a gap between the two groups of supporting assemblies. Each group of supporting assemblies comprises a plurality of supporting seats, each of which is vertically installed on the base, and the upper end surfaces of all the supporting seats jointly form a curved surface which is the same as the upper end surface of the framework structure of the airfoil product component to be processed. The tensioning assembly comprises a plurality of tensioning rods. The two ends of each tensioning rod are respectively connected with the top of two corresponding supporting seats in the two groups of supporting assemblies, and are respectively used for fixing the two corresponding supporting seats. The precision of the airfoil product component butt joint shaft obtained based on the processing tool is high.

Description

Technical Field

[0001] This invention relates to a method for machining a reference shaft, specifically to a machining fixture and method for a mating shaft of a ceramic matrix composite airfoil product component. Background Technology

[0002] Ceramic matrix 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-size, high-precision composite components. Therefore, finished parts based on this type of material are usually made by preparing small-size parts and then integrating and assembling them online.

[0003] For ceramic matrix composite airfoil components, the skeleton structure has 2-5 mating shafts. During product assembly, these mating shafts serve as the installation reference, and the remaining skeleton parts are assembled and connected using pins and bolts according to assembly requirements. After the skeleton is assembled, the skin is installed using pins and screws. Therefore, the machining quality and precision of the mating shafts, as the installation reference, are particularly important.

[0004] In existing ceramic matrix composite (CMC) airfoil components, the skeleton structure is made of CMC, while the mating shaft is made of metal. The manufacturing process involves processing both separately and then assembling them together using bolts. However, during assembly, factors such as assembly precision, gap elimination, and bolt tightening force can easily lead to installation deviations in the mating shaft, resulting in installation accuracy that fails to meet design requirements. Furthermore, after assembly, the stress on the internal pins and bolts can cause high-temperature deformation during high-temperature deposition treatment, affecting the subsequent assembly and mating accuracy of the metal shaft, as well as the precision of the airfoil mating position. Summary of the Invention

[0005] The purpose of this invention is to solve the technical problem that the accuracy of the mating shaft of the airfoil product component obtained by the existing processing method cannot meet the design requirements, and to provide a processing tooling and method for the mating shaft of the airfoil product component made of ceramic matrix composite material.

[0006] To achieve the above objectives, the technical solution provided by this invention is as follows:

[0007] A machining fixture for the mating shaft of a ceramic matrix composite airfoil product component is characterized by including a base, a support unit, and a tensioning assembly.

[0008] The base is a rectangular plate structure, and the support unit includes two sets of support components symmetrically arranged along the axis of the base length direction. There is a gap between the two sets of support components to accommodate the skeleton structure of the wing surface product component to be processed.

[0009] Each support assembly comprises a plurality of support seats arranged along the length direction of the base, each support seat being vertically installed on the base, and the upper end faces of all the support seats jointly forming a curved surface consistent with the upper end face profile of the skeleton structure of the wing surface product component to be processed;

[0010] The tension assembly comprises a plurality of tension bars, both ends of each tension bar being connected with the top of two corresponding support seats in the two support assemblies respectively, and each tension bar being used for fixing the corresponding two support seats, and the butt joint shaft of the wing surface product component to be processed being located between two adjacent tension bars.

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

[0012] The bottom of the first bottom support is installed on the base, and the top is a slope surface matched with the lower end face of the skeleton structure of the wing surface product component to be processed, and is used for supporting the slope surface part of the lower end face of the skeleton structure.

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

[0014] Further, the support unit further comprises a second bottom support, the second bottom support being arranged close to the baffle plate and being installed on the base, and being located between the first bottom support and the baffle plate, and being used for supporting the horizontal part of the lower end face of the skeleton structure of the wing surface product component to be processed.

[0015] Further, the inner side face of each support seat is provided with one or more protrusions, and the protrusions of the two support assemblies away from the end of the support seat where the protrusion is located form an accommodating space, and the virtual surface formed by the protrusions on both sides of the accommodating space is consistent with the shape of the side face of the skeleton structure of the wing surface product component to be processed.

[0016] Further, the base is further provided with a lifting ring at each corner.

[0017] Meanwhile, the application further provides a processing method of the butt joint shaft of the wing surface product component of the ceramic matrix composite material, comprising the following steps:

[0018] Step 1: processing the wing surface product component semi-finished product according to the process requirements, wherein the wing surface product component comprises a skeleton structure and a plurality of butt joint shafts vertically arranged on the same side of the skeleton structure; and a 0.5-1mm allowance is left in the circumferential direction of the butt joint shaft;

[0019] Step 2: assembling the processing tool of the butt joint shaft of the wing surface product component of the ceramic matrix composite material, vertically placing the skeleton structure of the wing surface product component semi-finished product between the two support assemblies, and connecting the top of the corresponding two support seats with the tension bar, so that each butt joint shaft is located between two adjacent tension bars.

[0020] Step【3】, using a numerical control milling machine to sequentially finish machining each butt joint shaft to remove the excess amount;

[0021] Step【4】, taking the wing surface product component processed in step【3】 from the machining tooling, thereby completing the processing of the butt joint shaft of the ceramic matrix composite wing surface product component.

[0022] Further, step【2】 is specifically:

[0023] 2.1, assembling each support seat, the first bottom support, the second bottom support and the baffle with the base in each support assembly in the two sets of support assemblies according to the shape of the semi-finished product framework structure of the wing surface product component;

[0024] 2.2, vertically placing the framework structure of the semi-finished product of the wing surface product component between the two sets of support assemblies, so that the side of the framework structure provided with the butt joint shaft faces upward, defining the side of the framework structure away from the butt joint shaft as the lower end face thereof, then the inclined surface portion of the lower end face is in contact with the top of the first bottom support, the horizontal portion is in contact with the top of the second bottom support, and the end of the length direction away from the inclined surface portion is in contact with the side of the baffle close to the second bottom support; at the same time, one side face of the framework structure is in contact with the protrusions of each support seat in one set of support assemblies, and the other side face leaves a gap between the protrusions of each support seat in the other set of support assemblies;

[0025] 2.3, connecting each support seat in the other set of support assemblies with the other side face of the framework structure by using bolts, and connecting the top of the two support seats corresponding to each other in the two sets of support assemblies by using a brace, so that each butt joint shaft is located between two adjacent braces.

[0026] Further, in step【3】, when finishing machining, the brace close to the side to be machined of the butt joint shaft needs to be disassembled for step-by-step machining, and after the machining of one side is completed, the brace on that side is installed.

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

[0028] 1. The machining tooling for the butt joint shaft of the ceramic matrix composite wing surface product component provided by the present application comprises a base, a support unit and a tensioning assembly, wherein the support unit comprises two sets of support assemblies arranged symmetrically, used for accommodating the framework structure of the wing surface product component to be machined, each set of support assemblies comprises a plurality of support seats, and the tops of the support seats are tightly connected by a brace, the overall structure is simple, the wing surface product component to be machined can be quickly and stably fixed, and high-precision machining of the butt joint shaft is realized.

[0029] 2. The ceramic matrix composite wing surface product component butt joint shaft processing tool provided by the application is 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 precision.

[0030] 3. The ceramic matrix composite wing surface product component butt joint shaft processing tool provided by the application is provided with one or more protrusions on the inner side of each support seat, thereby avoiding damage to the surface of the framework structure caused by excessive contact between the support seat and the framework structure during processing.

[0031] 4. The ceramic matrix composite wing surface product component butt joint shaft processing tool provided by the application is simple to assemble and accurate in positioning, thereby ensuring that the precision of the butt joint shaft meets the design requirements.

[0032] 5. The ceramic matrix composite wing surface product component butt joint shaft processing method provided by the application is simple in processing mode, easy to operate and high in processing efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0033] Figure 1 FIG. 1 is a structural schematic diagram of a wing surface product component.

[0034] Figure 2 FIG. 3 is a structural schematic diagram of an embodiment of the ceramic matrix composite wing surface product component butt joint shaft processing tool.

[0035] Figure 3 FIG. 4 is a structural schematic diagram of a base in an embodiment of the ceramic matrix composite wing surface product component butt joint shaft processing tool.

[0036] Figure 4 FIG. 5 is a structural schematic diagram of a set of support assemblies in an embodiment of the ceramic matrix composite wing surface product component butt joint shaft processing tool.

[0037] Figure 5 FIG. 6 is an assembly structural schematic diagram of the ceramic matrix composite wing surface product component butt joint shaft processing tool and the wing surface product component to be processed.

[0038] The reference signs are as follows:

[0039] 1-base, 11-lifting ring, 2-support seat, 21-protrusion, 3-stay, 4-first bottom support, 5-baffle, 6-second bottom support, 7-framework structure, 8-butt joint shaft. DETAILED DESCRIPTION

[0040] In order to make the purposes, advantages and characteristics of the present application clearer, the following will make further detailed description of the present application in combination with the drawings and specific embodiments. Those skilled in the art should understand that these embodiments are only used to explain the technical principles of the present application, and the purpose is not to limit the protection scope of the present application.

[0041] As shown in Figure 2 , the present embodiment provides a processing tool for a ceramic matrix composite airfoil product component butt joint shaft, which comprises a base 1, a support unit and a tensioning assembly. In order to avoid the influence of external factors on the precision of the airfoil product component during assembly, as shown in Figure 1 , the present embodiment designs the component as a skeleton structure 7 and an integrated structure of the butt joint shaft 8, so as to improve the overall machining precision and the subsequent assembly precision.

[0042] In combination with Figure 1 and Figure 3 , the base 1 is a rectangular plate structure, the support unit comprises two groups of support assemblies which are symmetrically arranged along the axis of the length direction of the base 1, and there is a gap between the two groups of support assemblies for accommodating the skeleton structure of the airfoil product component to be machined.

[0043] 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 installed on the base 1, and the upper end faces of all the support seats 2 jointly form a curved surface consistent with the upper end face of the skeleton structure 7 of the airfoil product component to be machined.

[0044] The tensioning assembly comprises a plurality of tensioning strips 3; both ends of each tensioning strip 3 are connected with the top of two corresponding support seats 2 in the two groups of support assemblies respectively, for fixing the two corresponding support seats 2 respectively, and the butt joint shaft 8 of the airfoil product component to be machined is located between the adjacent two tensioning strips 3.

[0045] In order to provide the stability of support, the support unit further comprises a first bottom support 4 and a second bottom support 6 which are respectively installed on the base 1 between the two groups of support assemblies. Since one end of the side away from the butt joint shaft 8 of the skeleton structure 7 of the airfoil product component to be machined is a beveled structure and the other end is a horizontal structure, the top of the first bottom support 4 is designed as a bevel matched with the lower end face (i.e. the side away from the butt joint shaft 8) of the skeleton structure 7 of the airfoil product component to be machined, for supporting the beveled part of the lower end face of the skeleton structure 7, and the second bottom support 6 is used to support the horizontal part of the lower end face of the skeleton structure 7 of the airfoil product component to be machined.

[0046] Meanwhile, the present embodiment is provided with a baffle 5 on the base 1 for supporting the length direction end face of the skeleton structure 7 of the airfoil product component to be machined, so as to improve the stability of the airfoil product component to be machined during machining.

[0047] AsFigure 4 To avoid damaging the surface of the wing surface product component to be processed, one or more protrusions 21 are arranged on the inner side of each support seat 2 in the embodiment, and the protrusions 21 of all the support assemblies of the two groups of support assemblies form a containing space away from the end of the support seat 2 where the protrusions 21 are located, and the virtual surface formed by the protrusions 21 on both sides of the containing space is consistent with the shape of the two side surfaces of the framework structure of the wing surface product component to be processed.

[0048] The base 1 is provided with a lifting ring 11 at each corner, facilitating the movement and transportation of the tooling as a whole.

[0049] In addition, the application also provides a processing method of the ceramic matrix composite wing surface product component butt joint shaft processing tooling, which comprises the following steps:

[0050] Step 1: processing the wing surface product component semi-finished product according to the process requirements, wherein the wing surface product component comprises a framework structure 7 and a plurality of butt joint shafts 8 vertically arranged on the same side of the framework structure 7; at this time, the framework structure has been added to the finished product size, and the butt joint shaft 8 has a 0.5-1mm allowance in the circumferential direction.

[0051] Step 2: assembling the ceramic matrix composite wing surface product component butt joint shaft processing tooling, and vertically placing the framework structure 7 of the wing surface product component semi-finished product between the two groups of support assemblies, specifically:

[0052] 2.1, according to the shape of the framework structure 7 of the wing surface product component semi-finished product, assembling each support seat 2, first bottom support 4, second bottom support 6 and baffle 5 of the two groups of support assemblies with the base 1, wherein the height of the support seat 2 is matched and designed according to the width of the framework structure 7, the number of the support seat 2 is determined according to the number of the butt joint shaft 8, generally four support seats 2 correspond to one butt joint shaft 8, and the number of the stay 3 is determined according to the number of the support seat 2.

[0053] 2.2, vertically placing the framework structure 7 of the wing surface product component semi-finished product between the two groups of support assemblies, so that the side of the framework structure 7 provided with the butt joint shaft 8 faces upward, defining this side as the upper end surface of the framework structure 7, and the side away from the butt joint shaft 8 of the framework structure 7 as the lower end surface of the framework structure 7, then the inclined surface part of the lower end surface is in contact with the top of the first bottom support 4, the horizontal part is in contact with the top of the second bottom support 6, and the end of the length direction away from the inclined surface part is in contact with the side of the baffle 5 close to the second bottom support 6.

[0054] At the same time, one side of the framework structure 7 in the thickness direction is in contact with the protrusions 21 of each support seat 2 in one of the two groups of support assemblies, and the other side is left with a gap between the protrusions 21 of each support seat 2 in the other group of support assemblies.

[0055] 2.3, each support seat 2 in another group of support assemblies is connected with another side of the framework structure 7 by bolts, and two support seats 2 in the two groups of support assemblies are connected at the top by using a stay 3, so that each butt joint shaft 8 is located between two adjacent stays 3, as shown in Figure 5

[0056] Step 【3】, each butt joint shaft 8 is sequentially finished by using a numerical control milling machine, and the excess amount is removed. When finishing, in order to ensure the machining accuracy, the stay 3 near the butt joint shaft 8 to be machined on one side is disassembled, and is processed step by step. After the processing on one side is completed, the stay 3 on the side is installed, and all the butt joint shafts 8 are finished in this way.

[0057] Step 【4】, the wing surface product component after step 【3】 is taken off from the machining tooling, so that the processing of the butt joint shaft of the ceramic matrix composite wing surface product component is completed.

[0058] The machining accuracy of the butt joint shaft obtained based on the machining method of the embodiment is high, so that the installation reference of the wing surface product component and the remaining components is ensured, and the assembly accuracy and quality of the product are improved.

[0059] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.​

Claims

1. A processing tool for a ceramic matrix composite wing surface product component butt joint shaft, characterized in that: it comprises a base (1), a supporting unit and a tensioning assembly; the base (1) is a rectangular plate structure, the supporting unit comprises two groups of supporting assemblies symmetrically arranged along the axis of the length direction of the base (1) and a first bottom support (4) located between the two groups of supporting assemblies; there is a gap between the two groups of supporting assemblies for accommodating the framework structure of the wing surface product component to be processed; the bottom of the first bottom support (4) is mounted on the base (1), and the top is a slope matched with the lower end surface of the framework structure of the wing surface product component to be processed, for supporting the slope part of the lower end surface of the framework structure; each group of supporting assemblies comprises a plurality of supporting seats (2) arranged along the length direction of the base (1), each supporting seat (2) is vertically mounted on the base (1), and the upper end surfaces of all the supporting seats (2) together form a curved surface consistent with the upper end surface of the framework structure of the wing surface product component to be processed; the inner side surface of each supporting seat (2) is respectively provided with one or more protrusions (21), and the ends of all the protrusions (21) of the two groups of supporting assemblies away from the supporting seats (2) form an accommodation space, and the virtual surfaces formed by the protrusions (21) on both sides of the accommodation space are consistent with the shapes of the side surfaces of the framework structure of the wing surface product component to be processed; the tensioning assembly comprises a plurality of tensioning bars (3); the two ends of each tensioning bar (3) are respectively connected with the top of two corresponding supporting seats (2) in the two groups of supporting assemblies, respectively for fixing the two corresponding supporting seats (2), and the butt joint shaft of the wing surface product component to be processed is located between adjacent two tensioning bars (3). 2.The processing tool for a ceramic matrix composite wing surface product component butt joint shaft according to claim 1, characterized in that: a baffle (5) for supporting the length direction end surface of the framework structure of the wing surface product component to be processed is further arranged on the base (1). 3.The processing tool for a ceramic matrix composite wing surface product component butt joint shaft according to claim 2, characterized in that: the supporting unit further comprises a second bottom support (6) arranged close to the baffle (5) and mounted on the base (1), which is located between the first bottom support (4) and the baffle (5), for supporting the horizontal part of the lower end surface of the framework structure of the wing surface product component to be processed. 4.The processing tool for a ceramic matrix composite wing surface product component butt joint shaft according to claim 1, characterized in that: hoisting rings (11) are arranged at the four corners of the base (1).

5. A method of machining a ceramic matrix composite airfoil product member butt axis, characterized by, comprising the following steps: Step 1, processing the wing surface product component semi-finished product according to the process requirements, wherein the wing surface product component comprises a framework structure (7) and a plurality of butt joint shafts (8) vertically arranged on the same side of the framework structure (7); a 0.5-1mm allowance is left around the butt joint shaft (8). Step 【2】, the processing tool of the ceramic matrix composite airfoil product component butt joint shaft of any one of claims 1 to 4, the framework structure (7) of the airfoil product component semi-finished product is vertically placed between the two groups of support assemblies, and the corresponding two support seats (2) are connected at the top by the stay (3), so that each butt joint shaft (8) is located between two adjacent stays (3); Step 【3】, each butt joint shaft (8) is sequentially finished by using a numerical control milling machine, and the excess is removed; Step 【4】, the airfoil product component after step 【3】 is processed is taken off from the processing tool, so that the processing of the ceramic matrix composite airfoil product component butt joint shaft is completed.

6. The processing method for the mating shaft of the ceramic matrix composite airfoil product component according to claim 5, characterized in that, Step 【2】 is specifically: 2.1, according to the shape of the framework structure (7) of the airfoil product component semi-finished product, the assembly of each support seat (2), the first bottom support (4), the second bottom support (6) and the baffle (5) and the base (1) in the two groups of support assemblies is completed; 2.2, the framework structure (7) of the airfoil product component semi-finished product is vertically placed between the two groups of support assemblies, so that the side of the framework structure (7) provided with the butt joint shaft (8) faces upward, the side of the framework structure (7) away from the butt joint shaft (8) is defined as the lower end surface thereof, the inclined surface part of the lower end surface is in contact with the top of the first bottom support (4), the horizontal part is in contact with the top of the second bottom support (6), and the end of the length direction away from the inclined surface part is in contact with the side of the baffle (5) close to the second bottom support (6); at the same time, one side surface of the framework structure (7) is in contact with the protrusion (21) of each support seat (2) in one group of support assemblies, and the other side surface is spaced from the protrusion (21) of each support seat (2) in the other group of support assemblies; 2.3, each support seat (2) in the other group of support assemblies is connected with the other side surface of the framework structure (7) by using a bolt, and the top of the two support seats (2) corresponding to each other in the two groups of support assemblies is connected by using the stay (3), so that each butt joint shaft (8) is located between two adjacent stays (3).

7. The processing method of the ceramic matrix composite airfoil product component butt joint shaft according to claim 5 or 6, characterized in that: In step 【3】, when finishing, the stay (3) close to the side to be processed of the butt joint shaft (8) needs to be disassembled, and is processed step by step, and after the side is processed, the stay (3) on the side is installed.

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