Ceramic matrix composite rotor blade fiber preform and method of manufacture

Abstract

The application discloses a ceramic matrix composite rotor blade fiber preform and a manufacturing method. The rotor blade fiber preform comprises a blade body, a rim plate and a tenon which are connected into one body and formed by overlapping multiple fiber layers, the fiber layers are made of SiC fiber cloth, the tenon comprises a main body part, the main body part comprises two opposite tenon end faces and two tenon side faces which are adjacent to the two tenon end faces, the two side edges of the fiber layers correspond to the two tenon end faces respectively, the tenon side faces are action surfaces of the tenon, the two action surfaces are adapted to be in contact with two inner side walls of a tenon groove respectively, and the inclination angles of the action surfaces are adapted to be the same as the inclination angles of the corresponding inner side walls. In this way, after the rotor blade fiber preform is manufactured, chamfering treatment is performed on the two sides of the bottom of the main body part, a finished tenon is obtained, the fiber layers at the action surfaces are ensured to be continuous, the excellent performance of the ceramic matrix composite material is fully played, and the bearing capacity of the tenon and the bearing capacity of the rotor blade are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of fiber preform, in particular to a ceramic matrix composite rotor blade fiber preform and a manufacturing method. BACKGROUND

[0002] The ceramic matrix composite is mainly used for the turbine rotor blade structure of an aero-engine to play the material characteristics of high temperature resistance and low density of the ceramic matrix composite and improve the bearing capacity and fatigue life of the tenon head part.

[0003] At present, a scheme is proposed: without considering the stress characteristics of the tenon, a tenon blank of the ceramic matrix composite is prepared first, and then the appearance of the tenon is processed by mechanical processing.

[0004] However, since the stress of the tenon is not considered when the tenon blank is prepared, part of the fibers at the action surface of the tenon and the mortise are damaged and broken in the mechanical processing process, thereby weakening the bearing capacity of the tenon, and the tenon is prone to premature failure and reduced fatigue life, and the performance advantages of the ceramic matrix composite cannot be fully played.

[0005] In view of the above problems, it is necessary to design a new ceramic matrix composite rotor blade fiber preform and a manufacturing method. SUMMARY

[0006] Therefore, the technical problem to be solved by the present application is to prepare a tenon blank without considering the stress of the tenon, and part of the fibers at the action surface of the tenon will be broken in the process of obtaining the appearance of the tenon by mechanical processing of the tenon blank, which leads to premature failure of the tenon and reduces the fatigue life, thereby providing a ceramic matrix composite rotor blade fiber preform and a manufacturing method.

[0007] To solve the above technical problems, the technical scheme of the present application is as follows:

[0008] A ceramic matrix composite rotor blade fiber preform, the rotor blade fiber preform comprises a blade body, a rim plate and a tenon which are connected into one body and formed by overlapping laying of multiple fiber plies, the fiber plies are made of SiC fiber cloth, the tenon comprises a main body part, the main body part comprises two opposite tenon end faces and two tenon side faces adjacent to the two tenon end faces, two side edges of the fiber plies correspond to the two tenon end faces respectively, the tenon side face is the action surface of the tenon, the two action surfaces are adapted to be in contact with two inner side walls of the mortise respectively, and the inclination angle of the action surface is adapted to be the same as the inclination angle of the corresponding inner side wall.

[0009] Further, a fiber core is filled in a cavity formed by the fiber plies of the innermost layer on the main body part.

[0010] Further, the main body part is dovetail type.

[0011] Further, the tenon further comprises a transition part, two ends of the transition part are connected with the rim plate and the main body part respectively, the transition part is rectangular in cross section, and the structure profile of the blade body is curved surface.

[0012] Further, the multiple layers of the fiber lay-up are divided into continuous lay-up and outer lay-up outside the continuous lay-up, the continuous lay-up is continuously arranged in the core area of the rotor blade, the outer lay-up comprises blade body outer lay-up and tenon outer lay-up, the blade body outer lay-up is formed by extending from top to bottom across the top end of the continuous lay-up, two ends of the blade body outer lay-up are respectively outwardly bent and extended to form a first butt joint part, the tenon outer lay-up is formed by extending from bottom to top across the bottom end of the continuous lay-up, two ends of the tenon outer lay-up are respectively outwardly bent and extended to form a second butt joint part, and the two first butt joint parts and the two second butt joint parts are fixed together to form the rim plate.

[0013] The technical scheme of the present application has the following advantages:

[0014] 1. The ceramic matrix composite rotor blade fiber preform provided by the present application, since the two side edges of the fiber lay-up correspond to the two tenon end faces respectively, the tenon side face is the action face of the tenon, the two action faces are adapted to be in contact with the two inner side walls of the mortise respectively, and the inclination angle of each action face is adapted to be the same as that of the corresponding inner side wall, therefore, after the rotor blade fiber preform is prepared, suitable chamfering treatment is performed on the two sides of the bottom of the main body part, the tenon with the target shape is obtained, and after the chamfering treatment, the fiber lay-up at the action face is still continuous, thus the excellent performance of the ceramic matrix composite material can be fully played, the load bearing capacity of the tenon is improved, and further the load bearing capacity of the rotor blade is improved.

[0015] 2. The ceramic matrix composite rotor blade fiber preform provided by the present application, the cavity formed by the fiber lay-up in the innermost layer on the main body part is filled with a fiber core, in this way, the fiber volume fraction of the tenon is improved, and the fiber core can also support the fiber lay-up outwardly, thus the load bearing capacity and service life of the tenon can be further improved.

[0016] 3. The ceramic matrix composite rotor blade fiber preform provided by the present application, the multiple layers of fiber plies are divided into continuous plies and external plies located outside the continuous plies, the continuous plies are continuously arranged in the core area of the rotor blade, and the external plies include a blade body external ply and a tenon external ply, the blade body external ply extends from top to bottom across the top end of the continuous plies to form, and the two ends of the blade body external ply are respectively bent and extended outward to form a first butt joint part, the tenon external ply extends from bottom to top across the bottom end of the continuous plies to form, and the two ends of the tenon external ply are respectively bent and extended outward to form a second butt joint part, and the two first butt joint parts and the two second butt joint parts are fixed together to form a rim, such a fiber laying mode can avoid the premature breakage of the rotor blade on the one hand because the continuous plies are continuously laid in the core area, and on the other hand, the blade body external ply and the tenon external ply are laid separately, and the rim is formed between the blade body and the tenon, so that the bending degree in the fiber ply laying process can be reduced, and the processing difficulty and the risk of fiber ply breakage can be reduced, the loss of SiC fiber cloth is reduced, and the processing efficiency of the rotor blade preform is improved.

[0017] 4. The ceramic matrix composite rotor blade fiber preform provided by the present application, the main body part is dovetail-shaped, compared with the existing tooth-shaped main body part, the number of fiber ply bending can be reduced, the risk of fiber ply breakage can be reduced, the processing difficulty can be reduced, and the processing efficiency is improved.

[0018] A manufacturing method of a ceramic matrix composite rotor blade fiber preform, comprising the following steps:

[0019] S1, the shape of the rotor blade is designed, the rotor blade comprises a blade body, a rim and a tenon connected as one, the tenon comprises a main body part, the main body part comprises two tenon end faces and two tenon side faces adjacent to the two tenon end faces, the two tenon side faces serve as two acting surfaces adapted to contact two inner side walls of a mortise respectively, and the inclination angle of the acting surface is the same as the inclination angle of the corresponding inner side wall;

[0020] S2, multiple layers of fiber plies are laid outside the mold with reference to the appearance of the rotor blade, the fiber plies are made of SiC fiber cloth, the two side edges of the fiber ply corresponding to the tenon side face correspond to the two tenon end faces respectively, and the fiber ply corresponding to the tenon side face is laid parallel to the tenon side face.

[0021] Further, the following steps are further included:

[0022] S3, the mold is taken out, and a cavity is formed in the inner side of the fiber ply in the innermost layer on the main body part;

[0023] S4, a fiber core is filled in the cavity.

[0024] Further, in the step of S2, when overlapping and laying multiple fiber plies outside the mold with the profile of the rotor blade as a reference, first, multiple continuous plies are laid in the core area of the rotor blade, then, multiple outer blade plies are laid from top to bottom with the profile of the blade body as a reference, across the top end of the continuous plies, and two first abutting portions are formed by bending outward and laterally from both ends of the outer blade plies, and then, multiple outer tenon plies are laid from bottom to top with the profile of the tenon as a reference, across the bottom end of the continuous plies, and two second abutting portions are formed by bending outward and laterally from both ends of the outer tenon plies, and finally, the two first abutting portions and the two second abutting portions are fixed together to form the rim plate.

[0025] Further, the first abutting portion and the second abutting portion are fixed together by interweaving with stitching fibers.

[0026] Further, the profile of the blade body is curved, and the tenon further comprises a transition portion connecting the main body portion and the rim plate, and the transition portion has a rectangular cross section.

[0027] The application provides a manufacturing method of a ceramic matrix composite rotor blade fiber preform, and the ceramic matrix composite rotor blade fiber preform manufactured by the method has all the advantages of the ceramic matrix composite rotor blade fiber preform. BRIEF DESCRIPTION OF DRAWINGS

[0028] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the following will briefly introduce the drawings needed to be used in the description of the specific embodiments or the prior art. Obviously, the drawings described below are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0029] Figure 1 It is an enlarged schematic view of the internal fiber laying of the tenon without chamfering in the present application;

[0030] Figure 2 It is an enlarged schematic view of the internal fiber laying of the rotor blade in the present application;

[0031] Figure 3 It is a structural schematic view of the tenon after chamfering in the present application;

[0032] Figure 4 It is a structural schematic view of the finished rotor blade in the present application.

[0033] Explanation of reference signs:

[0034] 1, blade; 2, rib; 3, tenon; 31, main body part; 32, transition part; 33, tenon end face; 34, tenon side face; 4, fiber ply; 41, continuous ply; 42, outer ply; 421, blade outer ply; 422, tenon outer ply; 423, first abutment part; 424, second abutment part; 5, fiber core; 6, stitching fiber; a, cavity. DETAILED DESCRIPTION

[0035] The technical solutions of the present application will be described clearly and completely below in conjunction with the drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0036] In the description of the present application, it should be noted that the orientations or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0037] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0038] In addition, the technical features involved in the different embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0039] For the convenience of understanding, first introduce the ceramic matrix composite material, which includes SiC fiber and matrix, the fiber ply 4 referred to below is made of high-temperature-resistant, low-density SiC fiber cloth.

[0040] Example 1

[0041] As Figures 1 to 4As shown, the embodiment provides a ceramic matrix composite rotor blade fiber preform, the rotor blade fiber preform comprising a blade body 1, a rim plate 2 and a tenon 3 connected as a whole and formed by overlapping laying of multiple fiber plies 4.

[0042] It should be noted that, although Figure 4 The shape of the blade body 1 is shown as a rectangle, but the actual structure of the blade body 1 is a curved surface.

[0043] The tenon 3 comprises a dovetail-shaped main body part 31 and a transition part 32 connected with the main body part 31, and the transition part 32 is also connected with the rim plate 2. The main body part 31 comprises two opposite tenon end faces 33 and two tenon side faces 34 adjacent to the two tenon end faces 33. The two side edges of the fiber plies 4 corresponding to the main body part 31 correspond to the two tenon end faces 33, respectively. The tenon side faces 34 are the action surfaces of the tenon 3, and the two action surfaces are adapted to be in contact with the two inner side walls of the mortise, respectively, and the inclination angles of the action surfaces are adapted to be the same as the inclination angles of the corresponding inner side walls. In this way, after the rotor blade fiber preform is prepared, suitable chamfering treatment is performed on the bottom of the main body part 31 by mechanical processing or the like, and the finished tenon with the target shape can be obtained, and after the chamfering treatment, the fiber plies 4 at the action surfaces are still continuous, so that the excellent performance of the ceramic matrix composite material can be fully utilized, the load bearing capacity of the tenon 3 is improved, and the load bearing capacity of the rotor blade is improved.

[0044] In addition, the cavity a formed by the innermost fiber plies 4 on the main body part 31 is filled with a fiber core 5, and the fiber core 5 is a fiber cylinder obtained by winding a fiber cloth cylinder, and the fiber cloth here is still SiC fiber cloth. In this way, the fiber volume fraction of the tenon 3 can be improved, and the fiber core 5 can also support the fiber plies 4 outwardly, so that the load bearing capacity and service life of the tenon 3 can be further improved.

[0045] The fiber plies 4 are introduced as a whole as follows:

[0046] The multi-layer fiber plies 4 forming the rotor blade are divided into continuous plies 41 and outer plies 42 outside the continuous plies 41. Each continuous ply 41 is continuously laid in the core region of the rotor blade, while the outer plies 42 include a blade body outer ply 421 and a tenon outer ply 422. The blade body outer ply 421 is formed by extending downward from the top end of the continuous plies 41, and two first abutting portions 423 are formed by extending outward and transversely from the two ends of the blade body outer ply 421. The tenon outer ply 422 is formed by extending upward from the bottom end of the continuous plies 41, and two second abutting portions 424 are formed by extending outward and transversely from the two ends of the tenon outer ply 422. The two first abutting portions 423 and the two second abutting portions 424 are fixed together to form the aforementioned rim 2. Such a fiber laying method, on the one hand, can avoid premature breakage of the rotor blade due to the continuous laying of the continuous plies 41 in the core region, and on the other hand, the blade body outer ply 421 and the tenon outer ply 422 are laid separately, and the rim 2 is formed between the blade body 1 and the tenon 3, so that during the laying of the fiber plies 4, the fiber plies 4 corresponding to the blade body 1 do not need to be bent and twisted to a large extent to reach the area where the tenon 3 is located, but only need to be connected with the fiber plies 4 of the tenon 3 at the position of the rim 2. Thus, the degree of bending of the fiber plies 4 during laying can be reduced, the processing difficulty and the risk of breaking of the fiber plies 4 can be reduced, and the processing efficiency of the rotor blade preform can be improved.

[0047] In addition, in the present embodiment, the first abutting portions 423 and the second abutting portions 424 are stitched and woven with stitching fibers 6, and the material of the stitching fibers 6 is the same as that of the fiber plies 4.

[0048] In the present embodiment, the main body portion 31 is designed in a dovetail shape instead of a pentagon shape as in the finished rotor blade, in order to reduce the number of bending of the fiber plies 4, reduce the risk of breaking of the fiber plies 4, and improve the laying efficiency. Since the inclined surface formed by the chamfer is not the acting surface of the interaction between the tenon and the tenon groove, although the main body portion on the rotor blade preform needs to be chamfered at last, it has little effect on the load bearing capacity of the rotor blade.

[0049] Embodiment 2

[0050] As shown in Figures 1 to 4 The present embodiment provides a method for manufacturing a ceramic matrix composite rotor blade fiber preform, comprising the following steps:

[0051] S1. Design the shape of the rotor blade so that the rotor blade includes a blade body 1, a rim plate 2 and a tenon 3 connected as one piece. The tenon 3 includes a dovetail-shaped main body 31. The main body 31 includes two tenon end faces 33 and two tenon side faces 34 that are adjacent to the two tenon end faces 33. The two tenon side faces 34 serve as two working surfaces suitable for contacting the two inner side walls of the tenon groove respectively. The inclination angle of each working surface is the same as the inclination angle of the corresponding inner side wall. Specifically, the structural surface of the blade body 1 is a curved surface. The tenon 3 also includes a transition part 32 connecting the main body 31 and the rim plate 2. The cross-section of the transition part 32 is rectangular.

[0052] S2. Multiple fiber layups 4 are superimposed on the outside of the mold, using the rotor blade morphology as a reference. The fiber layups 4 are made of SiC fiber cloth, so that the two sides of the fiber layup 4 corresponding to the tenon side 34 correspond to the two tenon end faces 33 respectively. The fiber layup 4 corresponding to the tenon side 34 is laid parallel to the tenon side 34. Specifically, when superimposing multiple fiber layups 4 on the outside of the mold, using the rotor blade morphology as a reference, multiple continuous layups 41 are first laid in the core region of the rotor blade. Here, the core region refers to the area on the rotor blade where the blade body 1, the edge plate 2, and the tenon 3 all have the same thickness, wherein the thickness direction is... Figure 4 Perpendicular to the paper surface from a viewing angle, and then across the top of the continuous layer 41, multiple layers of leaf body outer layer 421 are laid from top to bottom, referring to the shape of the leaf body 1. The two ends of the leaf body outer layer 421 are bent outward laterally to form two first joint parts 423. Then, across the bottom of the continuous layer 41, multiple layers of tenon outer layer 422 are laid from bottom to top, referring to the shape of the tenon 3. The two ends of the tenon outer layer 422 are bent outward laterally to form two second joint parts 424. Then, the two first joint parts 423 and the two second joint parts 424 are fixed together by interlacing and weaving stitching fibers 6 to form the edge plate 2. The material of the stitching fibers 6 is the same as the material of the fiber layer 4.

[0053] S3. Remove the mold and form cavity a inside the innermost fiber layup 4;

[0054] S4. Fill the cavity a with fiber core 5. The fiber core 5 is a fiber cylinder obtained by winding fiber cloth. The fiber cloth here is still SiC fiber cloth. In this way, the fiber volume fraction of the tenon 3 can be increased. In addition, the fiber core 5 can also support the fiber lay-up 4 outward. Therefore, the load-bearing capacity and service life of the tenon 3 can be further improved.

[0055] In the embodiment, since the fiber lay 4 corresponding to the tenon side 34 is laid parallel to the tenon side 34, and the inclination angle of the tenon side 34 is the same as that of the corresponding inner side wall, after the rotor blade preform is made, the bottom of the main body 31 on both sides is respectively processed by machining or the like to form a suitable chamfer, so that the finished tenon of the target shape is obtained. After the chamfer processing, the corresponding fiber lay 4 at the action surface remains continuous, so that the excellent performance of the ceramic matrix composite material can be fully utilized, the load capacity of the tenon 3 is improved, and the load capacity of the rotor blade is improved. In addition, since the continuous lay 41 is used for continuous laying in the core region, the rotor blade can be prevented from flying off prematurely. On the other hand, since the outer lay 421 of the blade body and the outer lay 422 of the tenon are laid separately, and the rim 2 is formed between the blade body 1 and the tenon 3, during the laying of the fiber lay 4, the fiber lay 4 corresponding to the blade body 1 does not need to be bent and twisted at a large angle to reach the area where the tenon 3 is located, but only needs to be connected with the fiber lay 4 of the tenon 3 at the corresponding position of the rim 2. Thus, the bending degree of the fiber lay 4 during laying can be reduced, the processing difficulty and the risk of fiber lay 4 breaking can be reduced, and the processing efficiency of the rotor blade preform can be improved.

[0056] In the embodiment, the main body 31 is set to dovetail type instead of pentagonal shape of the finished rotor blade, in order to reduce the number of bending of the fiber lay 4, reduce the risk of fiber lay 4 breaking, and improve the laying efficiency. Since the inclined surface formed by the chamfer is not the action surface of the interaction between the tenon and the groove, although the main body of the rotor blade preform needs to be chamfered at last, it has little effect on the load capacity of the rotor blade.

[0057] Obviously, the above embodiment is only an example for clear illustration, and is not a limitation on the implementation. Based on the above description, other different forms of changes or variations can be made by those skilled in the art. Here, all the implementations do not need to be exhausted, and the obvious changes or variations derived therefrom are still within the protection scope of the present application.

Claims

1. A ceramic matrix composite rotor blade fiber preform, characterized by, The rotor blade fiber preform comprises a blade body (1), a rim plate (2) and a tenon (3) connected as a whole and formed by overlapping laying of multiple fiber plies (4), the fiber plies (4) are made of SiC fiber cloth, the tenon (3) comprises a main body part (31), the main body part (31) comprises two opposite tenon end faces (33) and two tenon side faces (34) adjacent to the two tenon end faces (33), two side edges of the fiber plies (4) correspond to the two tenon end faces (33) respectively, the tenon side faces (34) are action faces of the tenon (3), the two action faces are adapted to contact two inner side walls of a mortise respectively, and the inclination angle of each action face is adapted to be the same as the inclination angle of the corresponding inner side wall; The tenon (3) further comprises a transition part (32), two ends of the transition part (32) are connected with the rim plate (2) and the main body part (31) respectively, the transition part (32) has a rectangular cross section, and the structural profile of the blade body (1) is a curved surface.

2. The ceramic matrix composite rotor blade fiber preform of claim 1, wherein, The main body part (31) is filled with a fiber core (5) in a cavity (a) formed by the innermost layer of the fiber plies (4).

3. The ceramic matrix composite rotor blade fiber preform of claim 1, wherein, The main body part (31) has a dovetail shape.

4. The ceramic matrix composite rotor blade fiber preform of claim 1, wherein, The multiple fiber plies (4) are divided into continuous plies (41) and outer plies (42) outside the continuous plies (41), the continuous plies (41) are continuously laid in a core region of the rotor blade, the outer plies (42) comprise blade body outer plies (421) and tenon outer plies (422), the blade body outer plies (421) are formed by extending from top to bottom across top ends of the continuous plies (41), and first abutting parts (423) are formed by extending outward and transversely from two ends of the blade body outer plies (421), the tenon outer plies (422) are formed by extending from bottom to top across bottom ends of the continuous plies (41), and second abutting parts (424) are formed by extending outward and transversely from two ends of the tenon outer plies (422), and the two first abutting parts (423) and the two second abutting parts (424) are fixed together to form the rim plate (2).

5. A method of making a ceramic matrix composite rotor blade fiber preform, characterized by, The method comprises the following steps: S1, designing a shape of a rotor blade, so that the rotor blade comprises a blade body (1), a rim plate (2) and a tenon (3) connected as a whole, the tenon (3) comprises a main body part (31), the main body part (31) comprises two tenon end faces (33) and two tenon side faces (34) adjacent to the two tenon end faces (33), the two tenon side faces (34) are two action faces adapted to contact two inner side walls of a mortise respectively, and the inclination angle of each action face is the same as the inclination angle of the corresponding inner side wall; S2, laying multiple layers of fiber plies (4) outside the mold with reference to the profile of the rotor blade, the fiber plies (4) being made of SiC fiber cloth, the two side edges of the fiber plies (4) corresponding to the tenon side surface (34) correspond to the two tenon end surfaces (33) respectively, and the fiber plies (4) corresponding to the tenon side surface (34) are laid parallel to the tenon side surface (34).

6. The method of making a ceramic matrix composite rotor blade fiber preform of claim 5, wherein, Further comprising the following steps: S3, taking out the mold, forming a cavity (a) inside the innermost layer of the fiber plies (4) on the main body (31); S4, filling the cavity (a) with fiber core (5).

7. The method of making a ceramic matrix composite rotor blade fiber preform of claim 5, wherein, In the step of S2, when laying multiple layers of fiber plies (4) outside the mold with reference to the profile of the rotor blade, first lay multiple layers of continuous plies (41) in the core area of the rotor blade, then lay multiple layers of outer blade plies (421) from top to bottom with reference to the profile of the blade body (1) across the top end of the continuous plies (41), and form a first butt joint (423) by laying the two ends of the outer blade plies (421) outward and transversely, and then lay multiple layers of tenon outer plies (422) from bottom to top with reference to the profile of the tenon (3) across the bottom end of the continuous plies (41), and form a second butt joint (424) by laying the two ends of the tenon outer plies (422) outward and transversely, and fix the first butt joint (423) and the second butt joint (424) on the same side together to form the rim plate (2).

8. The method of making a ceramic matrix composite rotor blade fiber preform of claim 7, wherein, The first butt joint (423) and the second butt joint (424) are fixed together by interweaving with stitching fibers (6).

9. The method of making a ceramic matrix composite rotor blade fiber preform according to any one of claims 5-8, wherein, The structure profile of the blade body (1) is curved, and the tenon (3) further comprises a transition portion (32) connecting the main body (31) and the rim plate (2), and the cross section of the transition portion (32) is rectangular.

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