Split-coated ceramic matrix composite blade tenon laying layer structure and preparation process of split-coated ceramic matrix composite blade tenon laying layer structure

Abstract

The invention relates to a split-coated ceramic matrix composite blade tenon layering structure and a preparation process, the structure comprises a left side assembly and a right side assembly which are symmetrically arranged and are both of a coating structure, the coating structure comprises an intercalation block, a continuous layering block and a coating piece, and the continuous layering block and the coating piece are integrated with a blade body. The wrapping piece is located on the sides, close to each other, of the left side assembly and the right side assembly, the end, away from the blade body, of the continuous layering block is bent towards the side, away from the wrapping piece, of the continuous layering block to form a V-shaped groove matched with the layer inserting block, and the layer inserting block is installed in the V-shaped groove. And the wrapping sheet is bent towards one side close to the continuous layering block and wraps along the outer edges of the intercalation block and the continuous layering block. Compared with the prior art, the device has the advantages of high laying precision, high bearing capacity and the like.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine blade tenon structures, and in particular to a split-coated ceramic-based composite material blade tenon layup structure and a preparation process thereof. Background Art

[0002] In aircraft engine turbine rotor systems, the tenon joint, as a key connecting structure between the blades and the turbine disk, performs multiple load-transfer functions. Under high-speed rotation, the tenon not only needs to continuously withstand centrifugal loads, aerodynamic loads, and high-temperature thermal stresses from the blades, but also needs to safely and reliably transfer these loads to the turbine disk. These harsh operating conditions, coupled with high temperatures and complex stress fields, dictate that the tenon joint structure must possess excellent stress distribution characteristics and geometric fit accuracy to ensure the structural integrity and operational reliability of the entire rotor system under extreme operating conditions.

[0003] Ceramic-based composites (CMCs) possess excellent high-temperature strength and low density, enabling long-term, stable service in high-temperature environments. Using CMCs instead of high-temperature alloys to manufacture turbine rotor blades can significantly reduce the overall mass of the turbine system. Furthermore, CMCs offer strong designability, allowing for the design of tenon layups based on the structure's macroscopic properties (such as geometry and stress distribution), ensuring a reliable connection between the blade and the turbine disk.

[0004] For example, the invention with publication number CN118008483A discloses a combined ceramic-based composite material blade tenon structure, including left and right tenon-groove contact components, a tenon center component, a wedge-shaped reinforcement component and a rivet component. The left and right tenon-groove contact components are connected to the upper sides of the tenon center component through a rivet component and are located above the two wedge-shaped reinforcement components. The wedge-shaped reinforcement component is connected to the lower sides of the tenon center component through a rivet component.

[0005] When designing the layup of the above-mentioned ceramic-based composite turbine blades, inserts are usually used to form a protruding dovetail tenon. However, due to the drastic changes in the thickness of the tenon, frequent inserting operations are required, and the inserts are scattered between multiple layups, which increases stress discontinuities and possible crack initiation points. If the inserts are laid out in a concentrated manner, they may be squeezed out and fall off due to the combined effects of centrifugal loads and disc constraints during service. In addition, as the main load-bearing component of ceramic-based composites, the spatial arrangement of fibers has a significant impact on the strength, lifespan and other properties of the tenon. Therefore, when designing the tenon layup structure, the continuity of the fibers must be fully considered to ensure that the contact area between the tenon and the disc has sufficient load-bearing capacity. Summary of the Invention

[0006] The purpose of the present invention is to overcome the defect of the above-mentioned prior art that the inserts are laid together and may be squeezed out and fall off due to the combined action of centrifugal load and wheel constraint during service, and to provide a split-coated ceramic-based composite blade tenon layup structure and preparation process.

[0007] The purpose of the present invention can be achieved by the following technical solutions:

[0008] The present solution provides a split-wrapped ceramic-based composite blade tenon lamination structure, comprising a symmetrically arranged left component and a right component, both of which are clad structures, wherein the cladding structure comprises an intercalation block and a continuous lamination block and a cladding sheet integral with the blade body, wherein the cladding sheet is located on the side where the left component and the right component are close to each other, and the end of the continuous lamination block away from the blade body is bent toward the side away from the cladding sheet to form a V-shaped groove matching the intercalation block, and the intercalation block is installed in the V-shaped groove, and the cladding sheet is bent toward the side close to the continuous lamination block and clad along the outer edges of the intercalation block and the continuous lamination block.

[0009] Preferably, the covering sheet includes a fixed section, an arc-shaped covering section and an edge plate connecting section connected in sequence, the fixed section is a fiber cloth extending from the blade part, the arc-shaped covering section covers the bottom end and side edge of the tenon, and the edge plate connecting section is perpendicular to the blade.

[0010] Preferably, the continuous ply block is a multi-layer laying structure, including an installation section and a bending section, the installation section is a fiber cloth extending from the blade part, and the bending section and the fixing section form a V-shaped groove.

[0011] Preferably, the intercalation block comprises a plurality of inserts, which are stacked in sequence, and each insert is made by laying SiC fiber cloth.

[0012] Preferably, the inserts are inserted into the V-shaped groove along the inclined direction of the bent end of the continuous ply block, and the inserts are stacked from one side of the V-shaped groove close to the continuous ply block to the other side.

[0013] This solution also provides a process for preparing a split-clad ceramic matrix composite blade tenon laminate structure, comprising the following steps:

[0014] S1: Extend and lay the SiC fiber cloth on the blade part to obtain continuous layup blocks and covering sheets;

[0015] S2: bending and shaping the continuous ply block toward a side away from the covering sheet to form a V-shaped groove between the continuous ply block and the covering sheet;

[0016] S3: Obtain an intercalation block that matches the shape of the V-shaped groove, and install the intercalation block into the V-shaped groove;

[0017] S4: bending the covering sheet along the outer edges of the insert block and the continuous ply block so that the end of the covering sheet fits in with the continuous ply block at the upper portion of the tenon;

[0018] S5: Obtain the left component and the right component according to steps S1-S4, and assemble the covering sheet sides of the left component and the right component into one body to obtain a blade tenon structure.

[0019] Furthermore, the intercalation block includes a plurality of inserts, which are stacked in sequence. The specific steps of installing the inserts into the V-shaped grooves are as follows:

[0020] Cut the inserts according to the structure of the V-shaped groove, and insert each insert into the V-shaped groove in sequence according to the inclined direction of the bent end of the continuous ply block, so that the length of the insert decreases from one side of the V-shaped groove close to the continuous ply block to the other side;

[0021] Each time the insert is inserted into the V-shaped groove, press the insert tightly. After all the inserts are inserted, use the shaping glue to fix them in place.

[0022] Furthermore, the insert includes a gap-filling insert and multiple filling inserts, and the gap-filling insert has a reserved installation length. The specific installation process is: install the filling insert into the V-shaped groove to form a gap with the side of the V-shaped groove close to the covering sheet; fill the gap with the filling insert and shape it with shaping glue; when the insert is shaped, cut the reserved installation length of the gap-filling insert to make the bottom end of the interlayer block flush.

[0023] Furthermore, the insert includes filled SiC fiber filaments and multiple filling inserts. The specific installation process is: install the filling insert into the V-shaped groove to form a gap with the side of the V-shaped groove close to the covering sheet, and fill the filling SiC fiber filaments into the gap; press the SiC fiber filaments until they are flush with the bottom end of the insert block, and then shape it with shaping glue.

[0024] Furthermore, the specific wrapping steps of the wrapping sheet are: the wrapping sheet is bent in sequence along the bottom end of the intercalation block and the outer edge of the bent end of the continuous layer block; the end of the wrapping sheet is bent into an edge plate connecting section that matches the edge plate through a mold, and finally shaped by a shaping glue.

[0025] Compared with the prior art, the present invention has the following advantages:

[0026] (1) This solution splits the blade tenon into two symmetrically arranged covering structures, and splits the blade extension structure into an outer continuous ply block and an inner covering sheet. The outer continuous ply block is bent to form a V-shaped groove with the covering sheet. The intercalation block is installed in the V-shaped groove and is bent outward by the inner covering sheet to cover the bent end of the continuous ply block and the intercalation block. By splitting the tenon into two parts, the preparation of the tenon is facilitated and the laying accuracy is ensured. In addition, the split covering method covers the intercalation block and the bent part, which reduces the possibility of the intercalation block being squeezed out or falling off due to the combined action of centrifugal load and wheel constraint during operation, further improving the load-bearing capacity and service life of the tenon.

[0027] (2) This solution adopts a left-right split wrapping method. Compared with the structural design of dispersed inserts, the inserts are laid in a centralized manner, which reduces the difficulty of tenon preparation. In addition, the coating process used allows the fibers in the middle of the tenon to extend from the blade body through the bottom of the tenon to the edge plate area, forming a complete fiber reinforcement path, enhancing the centrifugal load capacity of the structure and helping to improve the reliability and service life of the overall connection.

[0028] (3) This solution splits the blade tenon into two symmetrically arranged left and right components. After the two components are prepared using a coating structure, the left and right components are combined into an integrated structure. The modular design and preparation can improve the preparation efficiency of the tenon and reduce the preparation difficulty, which effectively ensures the laying accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a schematic diagram of the structure in which the tenon is divided into left and right components and then divided into a covering sheet, an insert block and a continuous lay-up block in the present invention;

[0030] Figure 2 Schematic diagram of the laying, bending and shaping of the continuous ply blocks in the present invention;

[0031] Figure 3 This is a schematic diagram of the inserts in the present invention being inserted into the V-shaped groove in the order of the numbers along the direction of the arrows and then being shaped;

[0032] Figure 4 This is a schematic diagram of the wrapping sheet extending from the blade body, bending along the continuous ply block and the insert block, and fitting with the continuous ply block at the upper portion of the tenon in the present invention;

[0033] Figure 5 Schematic diagram of the covering sheet turning over along the mold at the top of the tenon in the present invention;

[0034] Figure 6Schematic diagram of a dovetail joint of a ceramic matrix composite material turbine blade with left and right separate covers made of SiC fiber cloth, formed by combining left and right components formed by a covering sheet, a continuous layup block, and an intercalation block in the present invention;

[0035] In the figure: 1, left component, 2, right component, 3, continuous lay-up block, 4, insert block, 5, covering piece, 6, first insert, 7, second insert, 8, third insert, 9, fourth insert, 10, fifth insert, 11, sixth insert, 12, seventh insert, 13, eighth insert, 14, ninth insert, 15, tenth insert, 31, installation section, 32, bending section, 51, fixing section, 52, arc-shaped covering section, 53, edge plate connecting section. DETAILED DESCRIPTION

[0036] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0037] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.

[0038] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0039] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, or are the orientation or position relationship in which the product of the invention is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they should not be understood as limiting the present invention.

[0040] It should be noted that the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, "plurality" means two or more, unless otherwise specifically defined.

[0041] Furthermore, terms such as "horizontal" and "vertical" do not necessarily mean that a component must be absolutely horizontal or overhanging, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but rather that it can be slightly tilted.

[0042] Example 1

[0043] like Figure 1 and Figure 6 As shown, this embodiment provides a split-coated ceramic-based composite blade tenon laminate structure, including a symmetrically arranged left component 1 and a right component 2, both of which are coated structures. The coating structure includes an intercalation block 4 and a continuous laminate block 3 and a coating sheet 5 that are integrated with the blade body. The coating sheet 5 is located on the side where the left component 1 and the right component 2 are close to each other. The end of the continuous laminate block 3 away from the blade body is bent toward the side away from the coating sheet 5 to form a V-shaped groove that matches the intercalation block 4. The intercalation block 4 is installed in the V-shaped groove, and the coating sheet 5 is bent toward the side close to the continuous laminate block 3 and coated along the outer edges of the intercalation block 4 and the continuous laminate block 3.

[0044] The blade tenon is split into two symmetrically arranged covering structures, and the blade extension structure is split into an outer continuous ply block 3 and an inner covering sheet 5. The outer continuous ply block 3 is bent to form a V-shaped groove with the covering sheet 5. The intercalation block 4 is installed in the V-shaped groove and is bent outward by the inner covering sheet 5, covering the bent end of the continuous ply block 3 and the intercalation block 4. By splitting the tenon into two parts, the preparation of the tenon is facilitated and the laying accuracy is ensured. The split covering method also covers the intercalation block 4 and the bent portion, reducing the possibility of the intercalation block 4 being squeezed out or falling off due to the combined effects of centrifugal load and wheel disc constraints during operation, further improving the load-bearing capacity and service life of the tenon.

[0045] Preferred embodiment, as Figure 4 and Figure 5 As shown, the covering sheet 5 includes a fixed section 51, an arc-shaped covering section 52 and an edge plate connecting section 53 connected in sequence. The fixed section 51 is a fiber cloth extending from the blade body. The arc-shaped covering section 52 covers the bottom end and side edge of the tenon. The edge plate connecting section 53 is perpendicular to the blade body.

[0046] The use of a split left-right cladding method allows for centralized placement of the inserts, compared to a structure with dispersed inserts, reducing the complexity of tenon fabrication. Furthermore, the cladding process allows the fibers in the middle of the tenon to extend from the blade body through the tenon base to the edge plate area, forming a complete fiber reinforcement path. This enhances the centrifugal load capacity of the structure and helps improve the reliability and service life of the overall connection.

[0047] like Figure 2 As shown, the continuous ply block 3 is a multi-layered structure, including a mounting section 31 and a bending section 32 . The mounting section 31 is a fiber cloth extending from the blade portion, and the bending section 32 and the fixing section 51 form a V-shaped groove.

[0048] In this embodiment, Figure 3 As shown, the intercalation block 4 includes a plurality of inserts, which are stacked in sequence, and each insert is made by laying SiC fiber cloth.

[0049] Furthermore, the inserts are inserted into the V-shaped groove along the inclined direction of the bent end of the continuous ply block 3 , and the inserts are stacked from one side of the V-shaped groove close to the continuous ply block 3 to the other side.

[0050] like Figures 1 to 6 As shown, this embodiment also provides a preparation process for a split-clad ceramic matrix composite blade tenon layup structure, comprising the following steps:

[0051] S1: Extend and lay the SiC fiber cloth on the blade part to obtain a continuous layup block 3 and a covering sheet 5;

[0052] S2: bending and shaping the continuous ply block 3 toward the side away from the covering sheet 5 to form a V-shaped groove between the continuous ply block 3 and the covering sheet 5;

[0053] S3: Obtain an intercalation block 4 that matches the shape of the V-shaped groove, and install the intercalation block 4 into the V-shaped groove;

[0054] S4: Bend the covering sheet 5 along the outer edges of the intercalation block 4 and the continuous ply block 3 so that the end of the covering sheet 5 fits in contact with the continuous ply block 3 at the upper portion of the tenon;

[0055] S5: Obtain the left component 1 and the right component 2 according to steps S1-S4, and assemble the covering sheet sides of the left component 1 and the right component 2 into one body to obtain a blade tenon structure.

[0056] In this embodiment, the intercalation block 4 includes a plurality of inserts, which are stacked in sequence. The specific steps for installing the inserts into the V-shaped grooves are as follows:

[0057] Cut the inserts according to the structure of the V-shaped groove, and insert each insert into the V-shaped groove in sequence according to the inclination direction of the bending section of the continuous ply block 3, so that the length of the insert decreases from one side of the V-shaped groove close to the continuous ply block 3 to the other side;

[0058] Each time the insert is inserted into the V-shaped groove, press the insert tightly. After all the inserts are inserted, use the shaping glue to fix them in place.

[0059] In this embodiment, the insert includes a gap-filling insert and multiple filling inserts. The gap-filling insert has a reserved installation length. The specific installation process is: install the filling insert into the V-shaped groove to form a gap with the side of the V-shaped groove close to the covering sheet 5; fill the gap with the filling insert and shape it with shaping glue; when the insert is shaped, cut the reserved installation length of the gap-filling insert so that the bottom end of the intercalation block 4 is flush.

[0060] In this embodiment, the insert includes filled SiC fiber filaments and multiple filled inserts. The specific installation process is: install the filled insert into the V-shaped groove to form a gap with the side of the V-shaped groove close to the covering sheet 5, and fill the filled SiC fiber filaments in the gap; press the SiC fiber filaments until they are flush with the bottom end of the intercalation block 4, and then shape them with shaping glue.

[0061] In this embodiment, the specific wrapping steps of the wrapping sheet 5 are: the wrapping sheet 5 is bent in sequence along the bottom end of the intercalation block 4 and the outer edge of the bent end of the continuous laying block 3; the end of the wrapping sheet 5 is bent into an edge plate connecting section that cooperates with the edge plate through a mold, and finally shaped by a shaping glue.

[0062] In combination with the above-mentioned preferred embodiment, this embodiment provides a more specific split-coated ceramic-based composite blade dovetail tenon layup structure, including a left component 1 and a right component 2, wherein the left component 1 and the right component 2 have the same structure and are symmetrically arranged, and are both coated structures, consisting of an intercalation block 4, a continuous layup block 3 and a coating sheet 5.

[0063] The continuous ply block 3 is laid as an extension of the SiC fiber cloth on the blade airfoil, ensuring continuous stress transfer from the blade airfoil to the tenon. The continuous ply block is bent in the mold based on the angle of the tenon groove and fixed with glue to ensure a precise fit with the tenon groove surface. The continuous ply blocks 3 of the left and right components 1 and 2 are bent separately, requiring fewer layers and reducing the bending difficulty.

[0064] A V-shaped groove is formed between the bent section 32 of the continuous ply block 3 and the fixed section 51 of the covering cloth 5, which is used to install the intercalation block 4. The intercalation block 4 of the left component 1 and the right component 2 each contains 10 inserts, which are cut according to the designed geometric dimensions. After stacking, the entire block fits into the V-shaped groove. The intercalation block 4 includes a first insert 6, a second insert 7, a third insert 8, a fourth insert 9, a fifth insert 10, a sixth insert 11, a seventh insert 12, an eighth insert 13, a ninth insert 14, and a tenth insert 15, with lengths decreasing. The 10 inserts are inserted into the V-shaped groove in order from longest to shortest, pressed tightly one by one, and then glued into shape.

[0065] Since the tenth insert 15 is very short and inconvenient to install, in order to ensure the accuracy of the laying, a certain installation length is reserved at the tail end of the tenth insert 15 during cutting. After the insert block 4 is shaped in the V-groove, a second cutting is performed to cut off the installation length reserved at the tail end of the tenth insert 15 to ensure that the bottom end of the insert block 4 is flush. If the vacant gap corresponding to the tenth insert 15 is very small, SiC fiber bundle can be used instead of the tenth insert 15 to fill the gap. Press the SiC fiber bundle into the gap so that it is flush with the bottom surface of the other inserts, and then use glue to shape it. Ensure that the bottom end of the insert block 4 and the edge of the bending section 32 of the continuous laying block 3 have a smooth transition, so that the arc-shaped covering section 52 of the covering cloth 5 fits closely with its outer edge, thereby improving the laying accuracy.

[0066] The covering sheet 5 is also made of SiC fiber cloth extending from the blade body to ensure the continuity of the fiber. Figure 4 As shown, after the insertion block 4 and the continuous ply block 3 are laid, the covering sheet 5 is bent along its outer edge based on the structure formed, and the end of the covering sheet 5 is fitted with the outer edge of the continuous ply block 3 at the upper part of the tenon. Figure 5 As shown, the covering sheet 5 is bent and then turned over at the top of the tenon using a mold to form an edge plate connecting section 53 that cooperates with the edge plate and is finally fixed in shape using glue.

[0067] Finally, if Figure 6 As shown, the opposite sides of the covering sheets of the left component 1 and the right component 2 are fitted and fixed to form a ceramic-based composite turbine blade tenon structure with left and right split coverings made of SiC fiber cloth.

[0068] The blade tenon is split into two symmetrically arranged left and right components. Each component is then individually coated and assembled into a single structure. This modular design and fabrication process improves tenon fabrication efficiency and reduces complexity, effectively ensuring layup accuracy. Furthermore, the left and right components utilize a separate coating process, encasing the intercalation block within. This reduces the likelihood of the intercalation block being squeezed out or dislodged during operation due to the combined effects of centrifugal loads and disc constraints, further improving the tenon's load-bearing capacity and service life.

[0069] The above describes in detail the preferred embodiments of the present invention. It should be understood that those skilled in the art can make numerous modifications and variations based on the concepts of the present invention without inventive effort. Therefore, any technical solutions that can be derived by those skilled in the art through logical analysis, reasoning, or limited experimentation based on the concepts of the present invention and the prior art should be within the scope of protection defined by the claims.

Claims

1. A split-clad ceramic-based composite blade tenon layup structure, characterized in that: The invention comprises a symmetrically arranged left component (1) and a right component (2), both of which are covering structures. The covering structure comprises an intercalation block (4), a continuous ply block (3) and a covering sheet (5) integrated with the blade body. The covering sheet (5) is located on a side where the left component (1) and the right component (2) are close to each other. An end of the continuous ply block (3) away from the blade body is bent toward a side away from the covering sheet (5) to form a V-shaped groove matching the intercalation block (4). The intercalation block (4) is installed in the V-shaped groove. The covering sheet (5) is bent toward a side close to the continuous ply block (3) and covers along the outer edges of the intercalation block (4) and the continuous ply block (3).

2. The split-clad ceramic matrix composite blade tenon laminate structure according to claim 1, characterized in that: The covering sheet (5) comprises a fixed section (51), an arc-shaped covering section (52) and an edge plate connecting section (53) connected in sequence, the fixed section (51) is a fiber cloth extending from the blade body portion, the arc-shaped covering section (52) covers the bottom end and side edge of the tenon, and the edge plate connecting section (53) is perpendicular to the blade body.

3. The split-clad ceramic matrix composite blade tenon laminate structure according to claim 2, characterized in that: The continuous ply block (3) is a multi-layered ply structure, comprising a mounting section (31) and a bending section (32); the mounting section (31) is a fiber cloth extending from the blade portion; the bending section (32) and the fixing section (51) form a V-shaped groove.

4. The split-clad ceramic matrix composite blade tenon layup structure according to claim 1, characterized in that: The intercalation block (4) comprises a plurality of inserts, which are stacked in sequence, and each insert is made by laying SiC fiber cloth.

5. The split-clad ceramic matrix composite blade tenon laminate structure according to claim 4, characterized in that: The inserts are inserted into the V-shaped groove along the inclined direction of the bent end of the continuous ply block (3), and the inserts are stacked from one side of the V-shaped groove close to the continuous ply block (3) to the other side.

6. A process for preparing a split-coated ceramic-based composite blade tenon laminate structure according to any one of claims 1 to 5, characterized in that: The following steps are involved: S1: Extend and lay the SiC fiber cloth on the blade part to obtain a continuous layup block (3) and a covering sheet (5); S2: bending and shaping the continuous ply block (3) toward a side away from the covering sheet (5) to form a V-shaped groove between the continuous ply block (3) and the covering sheet (5); S3: obtaining an intercalation block (4) that matches the shape of the V-shaped groove, and installing the intercalation block (4) into the V-shaped groove; S4: bending the covering sheet (5) along the outer edges of the intercalation block (4) and the continuous ply block (3) so that the end of the covering sheet (5) fits in contact with the continuous ply block (3) at the upper portion of the tenon; S5: Obtain the left component (1) and the right component (2) according to steps S1-S4, and assemble the left component (1) and the right component (2) into one piece by laminating the covering sheet sides to obtain a blade tenon structure.

7. The preparation process according to claim 6, characterized in that: The intercalation block (4) comprises a plurality of inserts, which are stacked in sequence. The specific steps of installing the inserts into the V-shaped grooves are as follows: Cutting the inserts according to the structure of the V-shaped groove, inserting each insert into the V-shaped groove in sequence according to the inclination direction of the bent end of the continuous ply block (3), so that the length of the insert decreases from one side of the V-shaped groove close to the continuous ply block (3) to the other side; Each time the insert is inserted into the V-shaped groove, press the insert tightly. After all the inserts are inserted, use the shaping glue to fix them in place.

8. The preparation process according to claim 7, characterized in that: The inserts include gap-filling inserts and a plurality of filling inserts, and the gap-filling inserts have a reserved installation length. The specific installation process is as follows: installing the filling insert into the V-shaped groove to form a gap with the side of the V-shaped groove close to the covering sheet (5); filling the gap with the gap-filling insert and shaping it with a shaping glue; after the inserts are shaped, cutting the reserved installation length of the gap-filling insert so that the bottom end of the intercalation block (4) is flush.

9. The preparation process according to claim 7, characterized in that: The insert comprises a filling SiC fiber and a plurality of filling inserts. The specific installation process is as follows: installing the filling insert into the V-shaped groove to form a gap with the side of the V-shaped groove close to the covering sheet (5), filling the filling SiC fiber into the gap; pressing the SiC fiber until it is flush with the bottom end of the insert block (4), and then shaping it with a shaping glue.

10. The preparation process according to claim 6, characterized in that: The specific coating steps of the coating sheet (5) are as follows: the coating sheet (5) is sequentially bent along the bottom end of the intercalation block (4) and the outer edge of the bent end of the continuous layer block (3); the end of the coating sheet (5) is then bent into an edge plate connecting section that matches the edge plate through a mold, and finally shaped by a shaping glue.

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