Prefabricated body of blade rotating shaft of ceramic matrix composite turbine rotor and forming method

Abstract

The invention relates to a ceramic-containing multilayer structure and a forming method, in particular to a prefabricated body of a blade rotating shaft of a turbine rotor made of a ceramic matrix composite material and a forming method, and aims to solve the technical problems of forming process limitation, structural layering and insufficient mechanical property when a current CMC material is applied to an aero-engine rotor blade rotating shaft. The prefabricated body of the blade rotating shaft of the ceramic matrix composite turbine rotor comprises a continuous layer assembly used for supporting, and a blade end reinforcing layer assembly and a rotating shaft end reinforcing layer assembly which are used for reinforcing, by means of the multi-layer design, stress concentration generated by a single material or a single-layer structure is reduced, and the risk of interlayer cracking is effectively reduced by reasonably distributing the thickness and the position of each layer of material.

Description

Technical Field

[0001] The invention relates to a ceramic-containing multilayer structure and a molding method, and in particular to a preform of a blade shaft of a turbine rotor made of ceramic-based composite material and a molding method. Background Art

[0002] In aircraft engines, the structure of the high-load rotor blade shaft usually includes a connecting plate, blades and shafts vertically arranged on both sides of the connecting plate, and the inner end of the shaft is used to connect to the wheel through a bearing system. Since key components such as rotor blades need to withstand extreme high temperatures, high pressures, strong corrosion and complex loads during operation, and traditional high-temperature alloy materials have reached their physical performance limits, it is difficult to meet the needs of the new generation of aircraft engines for higher service temperatures, lighter structures and longer life. Therefore, the development of revolutionary new materials has become the key.

[0003] Ceramic Matrix Composites (CMC) have become an advanced material widely concerned in the aviation field because they have the high strength, high hardness, high temperature resistance and corrosion resistance of ceramic materials, and improve the toughness and fatigue resistance of ceramics through composite fibers. CMC materials have the advantages of low density, impact resistance and long life, and are very suitable for high temperature and high load conditions. However, there are still some problems that need to be solved in the application of CMC materials in aircraft engine rotor blades.

[0004] In the prior art, the preparation of CMC materials mainly relies on the Chemical Vapor Infiltration (CVI) process, but this process has significant limitations in manufacturing complex structures, especially shaft components with large wall thickness and multiple curvatures. This causes the manufactured components to be prone to delamination defects, affecting their structural strength and stability, especially under high torque conditions, it is difficult to ensure their performance, thus hindering the application of CMC materials in high-load rotor blade shafts of aircraft engines. Summary of the invention

[0005] The purpose of the present invention is to solve the technical problems of the current CMC material application in aero-engine rotor blade shafts, such as molding process limitations, structural stratification, and insufficient mechanical properties, and to provide a preform and molding method for the blade shaft of a ceramic-based composite turbine rotor.

[0006] In order to solve the deficiencies of the above-mentioned prior art, the present invention provides the following technical solutions:

[0007] A preform of a blade shaft of a ceramic-based composite turbine rotor, which is special in that it comprises a continuous layer component, a blade end reinforcement layer component and a shaft end reinforcement layer component;

[0008] The continuous layer assembly includes a concave continuous layer and a convex continuous layer;

[0009] The concave continuous layer and the convex continuous layer both include a connecting plate, a blade plate and a rotating shaft plate respectively arranged vertically on the top and bottom surfaces of the connecting plate, the connecting plate of the concave continuous layer is arranged at the bottom end of the concave surface of the blade plate, and the connecting plate of the convex continuous layer is arranged at the bottom end of the convex surface of the blade plate;

[0010] The blade end reinforcement layer assembly includes a blade end concave reinforcement layer and a blade end convex reinforcement layer; the blade end concave reinforcement layer covers the top surface of the connecting plate and the concave surface of the blade plate of the concave continuous layer, and the blade end convex reinforcement layer covers the top surface of the connecting plate and the convex surface of the blade plate of the convex continuous layer;

[0011] The shaft end reinforcement layer assembly includes a first shaft end reinforcement layer and a second shaft end reinforcement layer; the first shaft end reinforcement layer covers the outer side surface of one shaft plate and the bottom surfaces of two connecting plates on the same side, and the second shaft end reinforcement layer covers the outer side surface of another shaft plate and the bottom surfaces of two connecting plates on the same side.

[0012] Furthermore, the ratio of the thickness of the connecting plate to the sum of the thickness of the first reinforcing layer at the rotating shaft end and the second reinforcing layer at the rotating shaft end covered on the connecting plate is 1:2;

[0013] The ratio of the sum of the thickness of the two blade plates to the sum of the thickness of the blade end concave reinforcement layer and the blade end convex reinforcement layer covered on the two blade plates is 1:2;

[0014] The ratio of the sum of the thicknesses of the two rotating shaft plates to the sum of the thicknesses of the first reinforcing layer at the rotating shaft end and the second reinforcing layer at the rotating shaft end covered on the two rotating shaft plates is 1:2.

[0015] Furthermore, the blade plates of the concave continuous layer and the blade plates of the convex continuous layer are arc surfaces with equal radii.

[0016] A method for forming a blade shaft based on a ceramic matrix composite material rotor is special in that it comprises the following steps:

[0017] Step 1, preparing a shaped metal tooling and a deposited graphite tooling according to the blade shaft;

[0018] The shaped metal tooling includes a concave metal tooling and a convex metal tooling; the concave metal tooling includes a blade tooling and a shaft tooling respectively adapted to the blade plate and the shaft plate of the concave continuous layer, and a connecting tool adapted to the / connecting plate of the concave continuous layer and located on the inner side of the shaft tooling; the convex metal tooling includes a blade tooling and a shaft tooling respectively adapted to the blade plate and the shaft plate of the convex continuous layer, and a connecting tool adapted to the / connecting plate of the convex continuous layer and located on the inner side of the shaft tooling;

[0019] The deposited graphite tooling includes a blade end concave tooling adapted to the blade end concave reinforcement layer, a blade end convex tooling adapted to the blade end convex reinforcement layer, a first shaft end tooling adapted to the first shaft end reinforcement layer, and a second shaft end tooling adapted to the second shaft end reinforcement layer; a plurality of sewing holes are provided on the blade end concave tooling, the blade end convex tooling, the shaft end first tooling, and the shaft end second tooling;

[0020] Step 2, laying fiber plain weave cloth layer by layer on the concave metal tooling and the convex metal tooling to prepare a concave continuous layer and a convex continuous layer respectively; then splicing the concave continuous layer and the convex continuous layer to obtain a continuous layer preform;

[0021] Step 3, by laying fiber plain weave cloth layer by layer on the blade end concave tooling, the blade end convex tooling, the shaft end first tooling, and the shaft end second tooling, respectively prepare the blade end concave reinforcement layer, the blade end convex reinforcement layer, the shaft end first reinforcement layer, and the shaft end second reinforcement layer;

[0022] Step 4, the continuous layer preform obtained in step 2, as well as the concave reinforcement layer at the blade end, the convex reinforcement layer at the blade end, the first reinforcement layer at the shaft end and the second reinforcement layer at the shaft end obtained in step 2 are assembled and fixed by bonding to obtain the preform of the blade shaft of the ceramic-based composite material rotor; the concave tooling at the blade end, the convex tooling at the blade end, the first tooling at the shaft end and the second tooling at the shaft end are used to press the preform, and two adjacent toolings are fixedly connected by bolts to obtain a deposited body;

[0023] Step 5, sewing the preform with carbon fiber through a plurality of sewing holes;

[0024] Step 6: Perform chemical vapor deposition on the deposited body processed in step 5 until the density of the preform reaches the preset requirement, remove the concave tooling at the blade end, the convex tooling at the blade end, the first tooling at the shaft end, and the second tooling at the shaft end, perform surface finishing, and obtain the blade shaft.

[0025] Furthermore, the step 2 is specifically as follows: laying the fiber plain weave cloth layer by layer on the concave surface of the blade tooling, the top surface of the connecting tooling and the outer surface of the shaft tooling of the concave metal tooling, and temporarily fixing each layer by bonding until the concave continuous layer is laid to the desired thickness, thereby obtaining a concave continuous layer;

[0026] The fiber plain weave cloth is laid layer by layer on the convex surface of the blade tooling, the top surface of the connecting tooling and the outer surface of the shaft tooling of the convex metal tooling, and each laid layer is temporarily fixed by bonding until the required convex continuous layer thickness is reached to obtain a convex continuous layer;

[0027] The concave continuous layer and the convex continuous layer are assembled and fixed by bonding to obtain a continuous layer preform.

[0028] Furthermore, the step 3 is specifically as follows: laying fiber plain weave cloth layer by layer on the inner sides of the concave tooling at the blade end, the convex tooling at the blade end, the first tooling at the shaft end, and the second tooling at the shaft end, and temporarily fixing each layer by bonding until the required preform thickness is reached, thereby obtaining the concave reinforcement layer at the blade end, the convex reinforcement layer at the blade end, the first reinforcement layer at the shaft end, and the second reinforcement layer at the shaft end, respectively.

[0029] Compared with the prior art, the present invention has the following beneficial effects:

[0030] (1) The present invention provides a preform of a blade shaft of a ceramic-based composite turbine rotor, comprising a continuous layer assembly for support, and a blade end reinforcement layer assembly and a shaft end reinforcement layer assembly for reinforcement; through a multi-layer design, the stress concentration generated by a single material or a single-layer structure is reduced, and by reasonably allocating the thickness and position of each layer of material, the risk of interlayer cracking is effectively reduced.

[0031] (2) The present invention provides a method for forming a blade shaft of a ceramic-based composite turbine rotor. The problems of interlayer cracking and fiber discontinuity are avoided by layered laying of fiber cloth and multiple tooling pressing. The problem of green body thickness is solved by reasonable thickness distribution and preform processing allowance control. The quality of vapor deposition is ensured by uniform pressing and high-temperature stable graphite fixing tooling. The torsional performance of the blade shaft is improved by strengthening layer design and torsional optimization of the layered structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a structural schematic diagram of an embodiment of a preform of a blade shaft of a turbine rotor of a ceramic-based composite material according to the present invention;

[0033] Figure 2 for Figure 1 Exploded diagram of

[0034] Figure 3 This is a schematic diagram of the structure of a concave continuous layer in an embodiment of the present invention;

[0035] Figure 4 This is a schematic diagram of the structure of a convex continuous layer in an embodiment of the present invention;

[0036] Figure 5 Schematic diagram of the structure of the concave reinforcement layer at the blade end in an embodiment of the present invention;

[0037] Figure 6 This is a schematic diagram of the structure of the convex reinforcement layer at the blade end in an embodiment of the present invention;

[0038] Figure 7 This is a schematic diagram of the structure of the first reinforcement layer at the end of the shaft in an embodiment of the present invention;

[0039] Figure 8 This is a schematic diagram of the structure of the second reinforcement layer at the end of the shaft in an embodiment of the present invention;

[0040] Fig. 9 It is a schematic structural diagram of a concave metal tooling in step 1 of an embodiment of a method for forming a blade shaft of a turbine rotor based on a ceramic-based composite material of the present invention;

[0041] Fig.10 Schematic diagram of the structure of the convex metal tooling in step 1 of the embodiment of the present invention

[0042] Fig.11 This is a schematic diagram of preparing a concave continuous layer preform in step 2 of an embodiment of the present invention;

[0043] Fig.12 This is a schematic diagram of preparing a convex continuous layer preform in step 2 of an embodiment of the present invention;

[0044] Fig.13 This is a schematic diagram of the structure of the continuous layer preform in step 2 of an embodiment of the present invention;

[0045] Fig.14 Schematic diagram of the structure of the deposited body in step 4 of an embodiment of the present invention.

[0046] The following are the descriptions of the reference numerals:

[0047] 100-continuous layer assembly, 101-blade plate, 102-connecting plate, 103-rotating shaft plate, 110-concave continuous layer, 120-convex continuous layer;

[0048] 200-blade end reinforcement layer assembly, 210-blade end concave reinforcement layer, 220-blade end convex reinforcement layer;

[0049] 300 - shaft end reinforcement layer assembly, 310 - shaft end first reinforcement layer, 320 - shaft end second reinforcement layer;

[0050] 410-concave metal tooling, 420-convex metal tooling;

[0051] 510-blade end concave tooling, 520-blade end convex tooling;

[0052] 610-first tooling at the end of the rotating shaft, 620-second tooling at the end of the rotating shaft;

[0053] 710-Stud graphite bolts, 720-Graphite nuts. DETAILED DESCRIPTION

[0054] The present invention will be further described below in conjunction with the accompanying drawings and exemplary embodiments.

[0055] Reference Figures 1 to 8A preform of a blade shaft of a ceramic-based composite turbine rotor includes a continuous layer assembly 100, a blade end reinforcement layer assembly 200 and a shaft end reinforcement layer assembly 300.

[0056] Reference Figures 1 to 4 , the continuous layer assembly 100 includes a concave continuous layer 110 and a convex continuous layer 120 .

[0057] The concave continuous layer 110 and the convex continuous layer 120 both include a connecting plate 102, blade plates 101 and a rotating shaft plate 103 vertically arranged on the top and bottom surfaces of the connecting plate 102, respectively. The connecting plate 102 of the concave continuous layer 110 is arranged at the bottom end of the concave surface of its blade plate 101, and the connecting plate 102 of the convex continuous layer 120 is arranged at the bottom end of the convex surface of its blade plate 101; the two blade plates 101 are arc surfaces with equal radius, which is convenient for processing and molding, reduces the complexity of the process, and also simplifies the installation process.

[0058] Reference Figure 1 , Figure 2 , Figure 5 , Figure 6 The blade end reinforcement layer assembly 200 includes a blade end concave reinforcement layer 210 and a blade end convex reinforcement layer 220; the blade end concave reinforcement layer 210 covers the top surface of the connecting plate 102 of the concave continuous layer 110 and the concave surface of the blade plate 101, and the blade end convex reinforcement layer 220 covers the top surface of the connecting plate 102 of the convex continuous layer 120 and the convex surface of the blade plate 101;

[0059] Reference Figure 1 , Figure 2 , Figure 7 , Figure 8 The shaft end reinforcement layer assembly 300 includes a first shaft end reinforcement layer 310 and a second shaft end reinforcement layer 320; the first shaft end reinforcement layer 310 covers the outer side surface of one shaft plate 103 and the bottom surfaces of two connecting plates 102 on the same side, and the second shaft end reinforcement layer 320 covers the outer side surface of another shaft plate 103 and the bottom surfaces of two connecting plates 102 on the same side.

[0060] The continuous layer assembly 100 plays a basic supporting and structural role, so it does not need to be too thick to avoid adding unnecessary weight. The blade end reinforcement layer assembly 200 and the shaft end reinforcement layer assembly 300 are responsible for strengthening the blade and the shaft end. By setting a thicker reinforcement layer, the strength and durability of these key parts can be increased. Specifically, the ratio of the thickness of the connecting plate 102 to the sum of the thickness of the first reinforcement layer 310 and the second reinforcement layer 320 of the shaft end covered on the connecting plate 102 is 1:2; the ratio of the sum of the thickness of the two blade plates 101 to the sum of the thickness of the concave reinforcement layer 210 and the convex reinforcement layer 220 of the blade end covered on the two blade plates 101 is 1:2; the ratio of the sum of the thickness of the two shaft plates 103 to the sum of the thickness of the first reinforcement layer 310 and the second reinforcement layer 320 of the shaft end covered on the two shaft plates 103 is 1:2.

[0061] Reference Figures 9 to 14 A method for forming a blade shaft of a turbine rotor based on a ceramic matrix composite material comprises the following steps:

[0062] Step 1, preparing a shaped metal tooling and a deposited graphite tooling according to the blade shaft;

[0063] Reference Fig. 9 , Fig.10 The shaped metal tooling includes a concave metal tooling 410 and a convex metal tooling 420; the concave metal tooling 410 is respectively adapted to the blade plate 101 and the shaft plate 103 of the concave continuous layer 110, and the connecting tooling is adapted to the 1 / 2 connecting plate 102 of the concave continuous layer 110 and is located on the inner side of the shaft tooling; the convex metal tooling 420 is respectively adapted to the blade plate 101 and the shaft plate 103 of the convex continuous layer 120, and the connecting tooling is adapted to the 1 / 2 connecting plate 102 of the convex continuous layer 120 and is located on the inner side of the shaft tooling;

[0064] Reference Fig.14 The deposited graphite tooling includes a blade end concave tooling 510 adapted to the blade end concave reinforcement layer 210, a blade end convex tooling 520 adapted to the blade end convex reinforcement layer 220, a first shaft end tooling 610 adapted to the shaft end first reinforcement layer 310, and a shaft end second tooling 620 adapted to the shaft end second reinforcement layer 320; a plurality of sewing holes are provided on the blade end concave tooling 510, the blade end convex tooling 520, the shaft end first tooling 610, and the shaft end second tooling 620;

[0065] Step 2: Reference Fig.11, laying fiber plain weave cloth layer by layer on the concave surface of the blade tooling, the top surface of the connecting tooling and the outer surface of the shaft tooling of the concave metal tooling 410, and temporarily fixing each laid layer by bonding (resin glue) until the concave continuous layer 110 is laid to the required thickness, thereby obtaining the concave continuous layer 110;

[0066] Reference Fig.12 , laying fiber plain weave cloth layer by layer on the convex surface of the blade tooling, the top surface of the connecting tooling and the outer surface of the shaft tooling of the convex metal tooling 420, and temporarily fixing each laid layer by bonding (resin glue) until the convex continuous layer 120 is laid to the required thickness, thereby obtaining the convex continuous layer 120;

[0067] Reference Fig.13 , the concave continuous layer 110 and the convex continuous layer 120 are assembled and fixed by bonding to obtain a continuous layer preform;

[0068] Step 3, laying fiber plain weave cloth layer by layer on the inner side of the blade end concave tooling 510, the blade end convex tooling 520, the shaft end first tooling 610, and the shaft end second tooling 620, and temporarily fixing each laid layer by bonding (resin glue) until the required preform thickness is laid, and respectively obtaining the blade end concave reinforcement layer 210, the blade end convex reinforcement layer 220, the shaft end first reinforcement layer 310, and the shaft end second reinforcement layer 320;

[0069] Step 4: Assemble the continuous layer preform obtained in step 2, and the blade end concave reinforcement layer 210, blade end convex reinforcement layer 220, shaft end first reinforcement layer 310 and shaft end second reinforcement layer 320 obtained in step 3 and fix them by bonding to obtain a preform; use the blade end concave tooling 510, blade end convex tooling 520, shaft end first tooling 610, shaft end second tooling 620 to press the preform, and use stud graphite bolts 710 and graphite nuts 720 to fix and connect two adjacent toolings to form a deposition body, such as Fig.14 As shown, the shape and size of the preform are precisely controlled, and the structural stability and material uniformity during the deposition process are guaranteed; the wall thickness of the preform is increased by 0.6mm in each part compared to the blade shaft, and the length and width boundaries are symmetrically increased by ≥6mm to ensure the later processing allowance;

[0070] In step 3 and step 4, the fiber plain cloth is carbon fiber or silicon carbide, and is cut 15-20 mm larger than the tooling;

[0071] Step 5, sewing the preform through multiple sewing holes using a 3K carbon fiber tow one hole two needle method;

[0072] Step 6: Perform chemical vapor deposition on the deposited body processed in step 5 until the density of the preform reaches 2.0-2.2 g / cm3, then remove the concave tooling 510 at the blade end, the convex tooling 520 at the blade end, the first tooling 610 at the shaft end, and the second tooling 620 at the shaft end, and obtain the blade shaft after surface finishing.

Claims

1. A preform of a blade shaft of a ceramic matrix composite turbine rotor, characterized in that: It comprises a continuous layer assembly (100), a blade end reinforcement layer assembly (200) and a shaft end reinforcement layer assembly (300); The continuous layer assembly (100) comprises a concave continuous layer (110) and a convex continuous layer (120); The concave continuous layer (110) and the convex continuous layer (120) both comprise a connecting plate (102), a blade plate (101) and a rotating shaft plate (103) respectively arranged vertically on the top and bottom surfaces of the connecting plate (102); the connecting plate (102) of the concave continuous layer (110) is arranged at the bottom end of the concave surface of the blade plate (101), and the connecting plate (102) of the convex continuous layer (120) is arranged at the bottom end of the convex surface of the blade plate (101); The blade end reinforcement layer assembly (200) comprises a blade end concave reinforcement layer (210) and a blade end convex reinforcement layer (220); the blade end concave reinforcement layer (210) covers the top surface of the connection plate (102) of the concave continuous layer (110) and the concave surface of the blade plate (101), and the blade end convex reinforcement layer (220) covers the top surface of the connection plate (102) of the convex continuous layer (120) and the convex surface of the blade plate (101); The shaft end reinforcement layer assembly (300) comprises a first shaft end reinforcement layer (310) and a second shaft end reinforcement layer (320); the first shaft end reinforcement layer (310) covers the outer side surface of one shaft plate (103) and the bottom surface of two connecting plates (102) on the same side, and the second shaft end reinforcement layer (320) covers the outer side surface of another shaft plate (103) and the bottom surface of two connecting plates (102) on the same side.

2. The preform of the blade shaft of a ceramic matrix composite turbine rotor according to claim 1, characterized in that: The ratio of the thickness of the connecting plate (102) to the sum of the thickness of the first reinforcing layer (310) at the rotating shaft end and the second reinforcing layer (320) at the rotating shaft end covered on the connecting plate (102) is 1:2; The ratio of the sum of the thicknesses of the two blade plates (101) to the sum of the thicknesses of the blade end concave reinforcement layer (210) and the blade end convex reinforcement layer (220) covered on the two blade plates (101) is 1:2; The ratio of the sum of the thicknesses of the two rotating shaft plates (103) to the sum of the thicknesses of the first rotating shaft end reinforcement layer (310) and the second rotating shaft end reinforcement layer (320) covered on the two rotating shaft plates (103) is 1:

2.

3. The preform of the blade shaft of a ceramic matrix composite turbine rotor according to claim 1 or 2, characterized in that: The blade plates (101) of the concave continuous layer (110) and the blade plates (101) of the convex continuous layer (120) are arc surfaces with equal radii.

4. A method for forming a blade shaft based on a ceramic matrix composite rotor, characterized in that: The steps include: Step 1, preparing a shaped metal tooling and a deposited graphite tooling according to the blade shaft; The shaped metal tooling includes a concave metal tooling (410) and a convex metal tooling (420); the concave metal tooling (410) includes a blade tooling and a shaft tooling respectively adapted to the blade plate (101) and the shaft plate (103) of the concave continuous layer (110), and a connecting tool adapted to the 1 / 2 connecting plate (102) of the concave continuous layer (110) and located on the inner side of the shaft tooling; the convex metal tooling (420) includes a blade tooling and a shaft tooling respectively adapted to the blade plate (101) and the shaft plate (103) of the convex continuous layer (120), and a connecting tool adapted to the 1 / 2 connecting plate (102) of the convex continuous layer (120) and located on the inner side of the shaft tooling; The deposited graphite tooling comprises a blade end concave tooling (510) adapted to the blade end concave reinforcement layer (210), a blade end convex tooling (520) adapted to the blade end convex reinforcement layer (220), a first shaft end tooling (610) adapted to the shaft end first reinforcement layer (310), and a shaft end second tooling (620) adapted to the shaft end second reinforcement layer (320); a plurality of sewing holes are provided on the blade end concave tooling (510), the blade end convex tooling (520), the shaft end first tooling (610), and the shaft end second tooling (620); Step 2: laying fiber plain weave cloth layer by layer on the concave metal tooling (410) and the convex metal tooling (420) to prepare a concave continuous layer (110) and a convex continuous layer (120) respectively; then, the concave continuous layer (110) and the convex continuous layer (120) are assembled to obtain a continuous layer preform; Step 3, by laying fiber plain weave cloth layer by layer on the blade end concave tooling (510), the blade end convex tooling (520), the shaft end first tooling (610), and the shaft end second tooling (620), respectively preparing the blade end concave reinforcement layer (210), the blade end convex reinforcement layer (220), the shaft end first reinforcement layer (310), and the shaft end second reinforcement layer (320); Step 4, assembling the continuous layer preform obtained in step 2, and the concave reinforcement layer (210) at the blade end, the convex reinforcement layer (220) at the blade end, the first reinforcement layer (310) at the shaft end, and the second reinforcement layer (320) at the shaft end obtained in step 3, and fixing them by bonding to obtain the preform of the blade shaft based on the ceramic-based composite material rotor according to claim 1; using the concave tooling (510) at the blade end, the convex tooling (520) at the blade end, the first tooling (610) at the shaft end, and the second tooling (620) at the shaft end to compress the preform, and fixing two adjacent toolings by bolts to obtain a deposited body; Step 5, sewing the preform with carbon fiber through a plurality of sewing holes; Step 6: Chemical vapor deposition is performed on the deposited body processed in step 5 until the density of the preform reaches the preset requirement, and then the concave tooling (510) at the blade end, the convex tooling (520) at the blade end, the first tooling (610) at the shaft end, and the second tooling (620) at the shaft end are removed, and the surface is trimmed to obtain the blade shaft.

5. The method for forming a blade shaft of a ceramic matrix composite turbine rotor according to claim 4, characterized in that: The step 2 specifically comprises: laying the fiber plain weave cloth layer by layer on the concave surface of the blade tooling, the top surface of the connecting tooling and the outer surface of the shaft tooling of the concave metal tooling (410), and temporarily fixing each laid layer by bonding until the concave continuous layer (110) is laid to the desired thickness, thereby obtaining the concave continuous layer (110); Laying fiber plain weave cloth layer by layer on the convex surface of the blade tooling, the top surface of the connecting tooling and the outer surface of the shaft tooling of the convex metal tooling (420), and temporarily fixing each laid layer by bonding until the convex continuous layer (120) is laid to the required thickness, thereby obtaining the convex continuous layer (120); The concave continuous layer (110) and the convex continuous layer (120) are assembled and fixed by bonding to obtain a continuous layer preform.

6. The method for forming a blade shaft of a ceramic matrix composite turbine rotor according to claim 4 or 5, characterized in that: The step 3 specifically comprises: laying fiber plain weave cloth layer by layer on the inner side surfaces of the concave tooling (510) at the blade end, the convex tooling (520) at the blade end, the first tooling (610) at the shaft end, and the second tooling (620) at the shaft end, and temporarily fixing each laid layer by bonding until the preform is laid to the required thickness, thereby respectively obtaining the concave reinforcement layer (210) at the blade end, the convex reinforcement layer (220) at the blade end, the first reinforcement layer (310) at the shaft end, and the second reinforcement layer (320) at the shaft end.

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