CN114893438A

CN114893438A - Composite material blade and processing method

Info

Publication number: CN114893438A
Application number: CN202210505541.4A
Authority: CN
Inventors: 康振亚; 郑会龙; 杨肖芳; 于浩; 李方; 陈晓奎; 张谭
Original assignee: Institute of Engineering Thermophysics of CAS
Current assignee: Institute of Engineering Thermophysics of CAS
Priority date: 2022-05-10
Filing date: 2022-05-10
Publication date: 2022-08-12
Anticipated expiration: 2042-05-10
Also published as: CN114893438B

Abstract

The invention provides a composite material blade and a processing method, comprising the following steps: the metal framework comprises lightening holes; a hollow curing unit insertingly disposed in the lightening hole; the flexible braided body is wrapped on the outer layers of the metal framework and the hollow curing unit. The impact resistance of the aero-engine blade is effectively improved, meanwhile, the weight of the composite material blade is reduced through the hollow structure, and the lightweight level of the composite material blade is effectively improved.

Description

Composite material blade and processing method

Technical Field

The invention relates to the field of aero-engine blades, in particular to a forming method for an aero-engine blade.

Background

The lightweight level of the aero-engine needs to be continuously improved for pursuing a high thrust-weight ratio, the composite material has the characteristics of high specific strength, high specific stiffness, good fatigue resistance and the like, and can effectively meet the characteristics of lightweight, fatigue resistance and the like of the aero-engine, so that the using amount and the occupation ratio of the composite material on the aero-engine are continuously improved. The aeroengine has a large number of blades and large mass, and the light weight of the aeroengine can effectively meet the actual use requirement of the future engine. The existing metal material blade has heavy weight and has stronger shock resistance, but can realize larger weight reduction only by introducing a composite material; the final composite material blade structure of the existing composite material blade is a solid structure no matter a layering hot pressing method or a three-dimensional weaving and RTM integrated curing forming method is adopted, the extremely weight reduction of the blade cannot be realized, and the impact resistance of the composite material blade which only adopts composite materials is poor. Therefore, a structure is needed that combines the advantages of strong impact resistance of the metal blade and weight reduction of the composite material blade.

Chinese patent CN202110637171, publication No. CN113547772A, published as 26/10/2021, discloses a method for manufacturing a fan blade with a hybrid structure, in which a metal leading edge is inserted into a composite material portion of the blade, and the metal leading edge portion and the composite material portion are joined by sewing with a sewing thread, but the composite material portion of the blade in the manufacturing process is a solid structure, and the fan blade with the hybrid structure does not achieve the maximum weight reduction goal. Chinese patent CN201711341200, publication No. CN108087318A, published as 2018, 05 and 29, discloses a composite material blade with a mixed structure, which comprises a titanium alloy matrix shaped like a Chinese character 'tian', and the outer surface of the titanium alloy matrix is covered with a thermoplastic skin to form a blade profile. Possible effects of this manufacturing process approach include: the blade composite material part is of a solid structure, and resin-based composite materials are filled in the Chinese character tian-shaped lightening holes, so that the aim of lightening the blades of the mixed-structure fan is not achieved to the maximum extent.

However, the existing composite material blade has insufficient shock resistance, the problem of impact delamination is easy to occur, the lightweight degree of the composite material blade needs to be further improved, and the requirement of extremely lightening weight cannot be met by a pure solid composite material blade.

Disclosure of Invention

In view of this, embodiments of the present disclosure provide a composite blade and a processing method thereof, so as to achieve the purpose of improving the impact resistance and the light weight of the composite blade.

The embodiment of the specification provides the following technical scheme:

a composite blade comprising:

the metal framework comprises lightening holes;

the hollow curing unit can be embedded in the lightening hole;

the flexible braided body is wrapped on the outer layers of the metal framework and the hollow curing unit.

Further, the hollow curing unit includes: the hollow curing unit splicing assembly comprises a hollow curing unit first splicing block, a hollow curing unit second splicing block and a hollow curing unit splicing assembly, wherein the hollow curing unit first splicing block and the hollow curing unit second splicing block are spliced into a hollow curing unit through the hollow curing unit splicing assembly.

Further, the hollow curing unit further includes: the outer layer of the solidification unit reinforcing rib is covered with the thermoplastic filling body, and the thermoplastic filling body and the solidification unit reinforcing rib form a weight reduction cavity together.

Further, the outer surface of the thermoplastic filling body is provided with a plurality of solidified unit bulges.

Further, the hollow curing units and the lightening holes can be arranged in a plurality of groups at intervals.

Furthermore, the metal framework is also provided with a plurality of threading holes, and the fiber tows fix the flexible woven body and the metal framework through the threading holes.

Furthermore, the composite material blade also comprises a front edge wrapping edge, the front edge wrapping edge is arranged at the front edge of the metal framework, and the flexible weaving body and the metal framework are wrapped and fixed through the front edge wrapping edge.

Further, the processing method of the composite material blade comprises the following steps:

step one, processing a metal framework and a hollow curing unit;

step two, fixedly installing the hollow curing unit on the metal framework;

step three, wrapping the flexible braided body outside the metal framework;

and step four, integrally solidifying and molding the metal framework, the hollow solidifying unit and the flexible braided body by using a thermoplastic filling body.

Further, in the first step, the processing method of the hollow curing unit specifically comprises the following steps:

fixing the curing unit protrusion on the metal mold in advance;

integrally solidifying and forming the solidification unit reinforcing ribs and the solidification unit bulges by using a thermoplastic filling body;

and splicing the first splicing blocks of the hollow curing units and the second splicing blocks of the hollow curing units together through the splicing assembly of the hollow curing units.

Further, the step of wrapping the metal framework with the flexible braided body comprises the following steps:

sleeving the flexible braided body on the metal framework;

the fiber tows penetrate through the flexible braided body and the threading holes of the metal framework so as to fix the metal framework and the flexible braided body;

the front edge part of the blade uses the front edge wrapping to encapsulate and fix the metal framework and the flexible braided body.

Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise:

the impact resistance of the aero-engine blade is effectively improved, meanwhile, hollowing of the composite material blade is achieved, and the lightweight level of the blade is effectively improved.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a general schematic view of a composite blade according to an embodiment of the invention;

FIG. 2 is a flow chart of a method of fabricating a composite blade according to an embodiment of the present invention;

FIG. 3 is a schematic diagram of a metal skeleton according to an embodiment of the present invention;

FIG. 4 is a schematic structural view of a hollow curing unit according to an embodiment of the present invention;

FIG. 5 is a side view of a hollow curing unit construction according to an embodiment of the present invention;

FIG. 6 is a side view of a metal skeleton construction according to an embodiment of the present invention;

FIG. 7 is a cross-sectional view of the portion of FIG. 6A-A in accordance with an embodiment of the present invention;

FIG. 8 is a schematic partial cross-sectional view of a composite blade according to an embodiment of the invention;

FIG. 9 is a schematic diagram of a first splice block of a hollow curing unit according to an embodiment of the present invention;

FIG. 10 is a cross-sectional view of the portion of FIG. 9B-B in accordance with an embodiment of the present invention;

FIG. 11 is a schematic illustration of a hollow curing unit according to an embodiment of the present invention prior to splicing;

FIG. 12 is a side view of a hollow curing unit after splicing in accordance with an embodiment of the present invention;

FIG. 13 is a schematic diagram of a hollow curing unit according to an embodiment of the present invention after splicing.

Description of the reference numerals: 1. a metal skeleton; 2. a flexible knitted body; 3. a hollow curing unit; 301. a curing unit reinforcing rib; 302. curing unit protrusions; 303. a thermoplastic filler; 304. a hollow curing unit first splice block; 305. a second splicing block of the hollow curing unit; 306. a hollow curing unit splicing component; 4. a tenon root; 5. a threading hole; 6. lightening holes; 7. and (6) edge wrapping of the front edge.

Detailed Description

Embodiments of the present application are described in detail below with reference to the accompanying drawings.

The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number and aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.

It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present application, and the drawings only show the components related to the present application rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.

In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.

The technical solutions provided by the embodiments of the present application are described below with reference to the accompanying drawings.

Referring to fig. 1, the inner layer of the composite material blade before the thermoplastic filler is solidified is composed of a metal framework 1, a plurality of lightening holes 6 are arranged on the metal framework 1, and the arrangement form of the lightening holes 6 can be in a row or in a fork row. The structure of the lightening holes 6 depends on the composite blade structure and the load bearing requirements. According to the shape of the metal framework 1 designed according to various requirements of the blade, a hollow curing unit 3 can be inserted into and fixed in a corresponding lightening hole 6, the space shape of the hollow curing unit 3 is matched with that of the metal framework 1, the hollow curing unit 3 is connected in the lightening hole 6 in a clamping mode through shape matching, two side faces of the hollow curing unit 3 can be a space plane or a curved surface and the like, and the two side faces of the metal framework 1 and the two side faces of the hollow curing unit 3 can be spliced into two space curved surfaces in smooth transition. The bottom of the metal framework 1 is provided with an integrally formed tenon root 4, and the tenon root 4 is used for integrally installing and fixing the blade. After the hollow curing unit 3 is installed in the lightening hole 6 of the metal framework 1, the flexible braided body 2 is sleeved outside the whole body, so that the connection between the flexible braided body 2 and the metal framework 1 before the thermoplastic filler is not cured is more compact and compact, and the impact resistance of the composite material blade after the thermoplastic filler is cured is enhanced.

Referring to fig. 3, the front edge (i.e. the gas inflow direction when the blade is working) of the metal framework 1 is provided with a front edge wrapping 7, and the front edge wrapping 7 and the metal framework 1 body can be integrally designed and manufactured. The front edge wrapping 7 wraps and fixes the edges of the metal framework 1 and the flexible woven body 2, so that the rigidity of the space structure of the metal framework 1 is improved, and the capability of the composite material blade for resisting the frontal impact of the barrier is also improved. Set up a plurality of through wires holes 5 on metal framework 1, through wires holes 5 can be used for passing the fibre silk bundle of weaving the body 2 the same material with the flexibility, and the fibre silk bundle passes through wires holes 5 winding, ligature and taut metal framework 1 and the flexible body 2 of weaving, and metal framework 1 and the flexible body 2 of weaving are closely fixed together for overall structure before the thermoplastic filling body is not solidified is compacter, inseparable, makes the combined material blade shock resistance after the thermoplastic filling body solidification stronger.

In other embodiments, the leading edge strip 7 may be manufactured separately and spatially separated from the metal skeleton 1, and the leading edge strip 7 may be adhesively secured to the cured composite blade with the thermoplastic filler.

Referring to fig. 4 and 5, the hollow curing unit 3 of the present embodiment is an externally closed cavity structure, and the cavity can reduce the weight of the entire blade. The cavity is filled with gas and the outside of the cavity shell is wrapped with a thermoplastic filler 303. The curing unit reinforcing ribs 301 can be arranged in the cavity to reinforce the strength of the cavity structure, the shell of the hollow curing unit 3 and the curing unit reinforcing ribs 301 are soaked and cured by the thermoplastic filling body, so that the thermoplastic filling body 303 is wrapped outside, and the inner cavity is filled with gas. The direction that solidification unit strengthening rib 301 is towards the surface can set up a plurality of solidification unit archs 302, solidification unit arch 302 and solidification unit strengthening rib 301 integrated into one piece, the protruding 302 structure of solidification unit is similar to the Z-pin structure for the effort between the hollow solidification unit 3 of reinforcing and the flexible 2 carbon fiber structures of weaving body, thereby promote the interlayer intensity of the combined material blade after the solidification of the thermoplastic filling body, and promote the holistic shock resistance of blade.

After the hollow curing unit 3 is embedded into the metal framework 1, the outer surfaces of the hollow curing unit 3 and the metal framework 1 are flush, namely the hollow curing unit 3 and the metal framework 1 have the same thickness and the same integral streamline, so that a smooth transition space curved surface is realized. The hollow curing unit 3 completes topology optimization design according to the stress condition of the blade, the operation condition and the pneumatic structure of the blade to form an optimal and maximum size structure, and the cavity inside the hollow curing unit is filled with gas, namely the composite material blade is finally a hollow part, so that the weight is lighter. The material of the curing unit protrusion 302 and the curing unit reinforcing rib 301 is titanium alloy. The thermoplastic filler 303 is an epoxy resin in this embodiment.

As shown in fig. 6 and 7, fig. 6 is a side view of the composite blade of the present embodiment before being cured. Fig. 7 is a cross-sectional view of section a-a of fig. 6. The metal framework 1 is embedded with a hollow curing unit 3 from a cross section view, and the tenon root 4 at the lower side of the metal framework 1 can be in a conical shape or an iris shape so as to be conveniently installed into an engine hub. The metal framework 1 and the hollow curing unit 3 are integrated by the flexible braided body 2 to form a unified composite material blade integral structure.

Fig. 8 is a front edge covering part of the composite material blade of the embodiment, and the front edge of the metal framework 1 comprises a covering structure: and a front edge wrapping 7. The leading edge strip 7 enables the flexible knitted body 2 to be inserted into the metal skeleton 1. The hollow curing unit 3 is embedded in the lightening hole 6 of the metal framework 1 before the thermoplastic filler of the composite material blade is cured. In the process of implementing the infiltration solidification of the thermoplastic filler, after the infiltration solidification of the thermoplastic filler, the surface of the hollow solidification unit 3 is melted and integrated with the thermoplastic filler to be reshaped, after the solidified layer of the thermoplastic filler is cooled, the hollow solidification unit 3, the metal framework 1 and the flexible braided body 2 are solidified into a whole, and finally the composite blade with the solidified layer of the thermoplastic filler is formed.

As shown in fig. 9 and 10, the hollow curing unit first splicing block 304 and the hollow curing unit second splicing block 305 are both made by solidifying the thermoplastic filler 303 with a metal mold. The hollow curing unit first tile 304 and the hollow curing unit second tile 305 are identical in body part, and only the hollow curing unit tile assembly 306 is different in shape. In the manufacturing process, the structure of the solidification unit bump 302 is fixed on a metal mold in advance, and the thermoplastic filler 303 is filled into the metal mold, so that the solidification unit bump 302 and the thermoplastic filler 303 are solidified and formed together. The surface shape of the hollow curing unit 3 is ensured by a metal mold, so that the surface of the hollow curing unit 3 can realize smooth transition after being embedded into the metal framework 1.

As shown in fig. 11, 12, and 13, the hollow curing unit splicing assembly 306 includes a recess and a protrusion that mate with each other. Wherein the recesses and protrusions are used to achieve spatial positioning of the hollow curing unit first tile 304 and the hollow curing unit second tile 305. The hollow cured unit first tile 304 and the hollow cured unit second tile 305 are positioned by the hollow cured unit tile assembly 306 and then secured together by bonding or other joining processes to form the final hollow cured unit 3.

Referring to fig. 2, an embodiment of the present application provides a method for manufacturing a composite blade, including the following steps:

s201, processing the metal framework 1 and the hollow curing unit 3.

The method mainly comprises the step of processing the metal framework 1 of the blade according to the shape and the process requirements of the blade. Specifically, the processing steps of the metal framework 1 include:

and S2011, processing and manufacturing the metal framework 1.

Specifically, the metal framework 1 is integrally provided with a tenon root 4 and a front edge wrapping 7, and a lightening hole 6 and a threading hole 5 are processed. The processing adopts the following technical methods including but not limited to: 3D printing a metal blank, then finishing the final metal framework shape by machining, directly machining a forge piece to the final blade shape by machining, and using an electric spark forming technology of a graphite electrode;

and S2012, performing surface treatment on the metal framework 1. Surface treatments typically include, but are not limited to, texturing, sand blasting, and methods of machining precision microstructures.

The hollow curing unit 3 can be manufactured by various methods, and in this embodiment, the hollow curing unit 3 can be formed by splicing an upper splice block and a lower splice block. The two splicing blocks are manufactured by solidifying the thermoplastic filling body 303 through the metal mold, in the manufacturing process, the structure of the solidification unit bulge 302 is fixed on the metal mold in advance, the thermoplastic filling body 303 is filled into the metal mold, and the solidification unit reinforcing rib 301, the solidification unit bulge 302 and the thermoplastic filling body 303 are solidified and formed together. Two splice pieces contain a plurality of for the concatenation recess and arch, and the cooperation of pegging graft with recess and arch for the concatenation, after fixing two hollow splice pieces, it is together fixed with it through bonding or other connection process, forms final hollow solidification unit 3 structure.

The surface shape of the hollow curing unit 3 is ensured by a metal mold, so that the space surface formed by the hollow curing unit 3 can realize smooth transition after the hollow curing unit is embedded into the metal framework 1.

Specifically, the steps of processing and manufacturing the hollow curing unit 3 comprise:

s2013, fixing the curing unit protrusions 302 on the metal mold in advance.

S2014, integrally curing and forming the curing unit reinforcing ribs 301 and the curing unit protrusions 302 using the thermoplastic filling body 303.

Specifically, in the metal mold, the curing unit protrusions 302 and the curing unit reinforcing ribs 301 are infiltrated and cured by using the thermoplastic filler 303 to form the hollow curing unit first splicing block 304, and the inner cavity is filled with gas or the thermoplastic filler. The hollow curing unit second tile 305 is made by the same method.

S2015, splicing the hollow curing unit first splicing block 304 and the hollow curing unit second splicing block 305 by the hollow curing unit splicing assembly 306.

Specifically, after the hollow curing unit first splicing block 304 and the hollow curing unit second splicing block 305 are positioned by the hollow curing unit splicing assembly 306, they are fixed together by bonding or other connection processes to form the final hollow curing unit 3.

And S202, fixedly mounting the hollow curing unit 3 on the metal framework 1.

Specifically, because the engine turbine fan blade is of a curved surface structure, the lightening hole 6 of each metal framework 1 corresponds to one hollow curing unit 3, the hollow curing unit 3 is embedded and fixed in the lightening hole 6 of the metal framework 1 according to the requirement of complete surface fitting, and the hollow curing unit 3 is flush with the surface of the metal framework 1.

And S203, wrapping the flexible braided body 2 outside the metal framework 1.

Specifically, the step of wrapping the metal framework 1 by the flexible braided body 2 comprises:

s2031, sleeving the flexible braided body 2 on the metal framework 1.

Specifically, the metal framework 1 embedded with the hollow curing unit 3 is sleeved into the sleeve of the manufactured flexible braided body 2 to form the composite material blade which is not cured by the thermoplastic filling body.

S2032, the fiber tows penetrate through the flexible braided body 2 and the threading holes 5 of the metal framework 1 to fix the metal framework 1 and the flexible braided body 2.

Specifically, the fiber tows penetrate through the threading hole 5 and two side faces of the flexible braided body 2 to fix the metal framework 1 and the flexible braided body 2, and finally, the fiber tows are used for sewing the interface of the flexible braided body 2.

S2033, the front edge part of the blade is sealed and fixed with the metal framework 1 and the flexible braided body 2 by the front edge wrapping 7.

Specifically, the front edge of the blade generally needs higher strength, and the metal framework 1 and the flexible woven body 2 are integrally encapsulated and fixed by the front edge binding 7 integrally formed with the metal framework 1.

And S204, integrally solidifying and molding the metal framework 1, the hollow solidifying unit 3 and the flexible braided body 2 by using a thermoplastic filling body 303.

Specifically, the composite material blade is finally subjected to infiltration solidification molding through a thermoplastic filler 303 solidification process, and in the injection process of the thermoplastic filler 303, the thermoplastic filler 303 on the outer layer of the hollow solidification unit 3 is partially melted and is fused with the newly entered thermoplastic filler 303 and solidified. In the implementation process, the hollow curing unit 3, the metal framework 1 and the flexible braided body 2 are subjected to infiltration, curing and molding by the thermoplastic filler 303, and finally the composite material blade with the thermoplastic filler cured layer can be formed, wherein the processes used for curing the thermoplastic filler comprise RTM (resin transfer molding) curing and other processes. And finally, carrying out surface treatment on the composite material blade after the thermoplastic filling body is solidified so as to meet the requirements of the final composite material blade on precision and surface roughness.

In this example, all the thermoplastic fillers used for curing were epoxy resins. Both the fiber tow and the flexible knitted body 2 are carbon fibers.

The composite material of the embodiment is suitable for the composite material blade of the turbofan engine, and can also be applied to other structures such as airplane wings and large-scale composite material parts. The fiber tow and the flexible braid 2 may be a combination of carbon fiber, carbon fiber-glass fiber, carbon fiber-optical fiber, and the like.

The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments can be referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for the method embodiments described later, since they correspond to the system, the description is simple, and for the relevant points, reference may be made to the partial description of the system embodiments.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A composite blade, comprising:

the metal framework (1), wherein the metal framework (1) comprises lightening holes (6);

a hollow curing unit (3), wherein the hollow curing unit (3) is embeddable in the lightening hole (6);

the flexible braided body (2) is wrapped on the outer layers of the metal framework (1) and the hollow curing unit (3).

2. A composite blade according to claim 1, wherein the hollow curing unit (3) comprises: the hollow curing unit splicing assembly comprises a hollow curing unit first splicing block (304), a hollow curing unit second splicing block (305) and a hollow curing unit splicing assembly (306), wherein the hollow curing unit first splicing block (304) and the hollow curing unit second splicing block (305) are spliced into a hollow curing unit (3) through the hollow curing unit splicing assembly (306).

3. A composite blade according to claim 1, wherein the hollow curing unit (3) further comprises: the outer layer of the solidification unit reinforcing rib (301) is covered with the thermoplastic filling body (303), and the thermoplastic filling body (303) and the solidification unit reinforcing rib (301) jointly form a weight-reducing cavity.

4. A composite blade according to claim 3, wherein the outer surface of the thermoplastic filler (303) is provided with a plurality of cured cell protrusions (302).

5. A composite blade according to claim 1, characterised in that the hollow curing units (3) and the lightening holes (6) are arranged in groups at intervals.

6. The composite material blade as claimed in claim 1, wherein the metal framework (1) is further provided with a plurality of threading holes (5), and the fiber tows fix the flexible braided body (2) and the metal framework (1) through the threading holes (5).

7. The composite blade according to claim 1, further comprising a leading edge covering (7), wherein the leading edge covering (7) is arranged at the leading edge of the metal framework (1), and the flexible woven body (2) and the metal framework (1) are wrapped and fixed through the leading edge covering (7).

8. A method of manufacturing a composite blade for use in making a composite blade according to any of claims 1 to 7, the method comprising the steps of:

step one, processing a metal framework (1) and a hollow curing unit (3);

step two, fixedly installing the hollow curing unit (3) on the metal framework (1);

step three, wrapping the flexible braided body (2) outside the metal framework (1);

and fourthly, integrally solidifying and molding the metal framework (1), the hollow solidifying unit (3) and the flexible braided body (2) by using a thermoplastic filling body (303).

9. The method for processing the composite material blade as claimed in claim 8, wherein in the first step, the hollow curing unit (3) is processed by the following specific steps:

fixing the curing unit protrusions (302) on the metal mold in advance;

integrally solidifying and forming the solidifying unit reinforcing ribs (301) and the solidifying unit bulges (302) by using a thermoplastic filling body (303);

splicing together the hollow cured unit first splice (304) and the hollow cured unit second splice (305) by a hollow cured unit splicing assembly (306).

10. The method for manufacturing a composite blade according to claim 8, wherein the step of wrapping the flexible braided body (2) around the metal skeleton (1) comprises the following steps:

sleeving the flexible braided body (2) on the metal framework (1);

the fiber tows penetrate through the flexible braided body (2) and the threading holes (5) of the metal framework (1) to fix the metal framework (1) and the flexible braided body (2);

the front edge part of the blade is used for encapsulating and fixing the metal framework (1) and the flexible braided body (2) by using a front edge wrapping (7).