CN117245943A - Composite material structure, manufacturing method of casing, casing and engine - Google Patents

Composite material structure, manufacturing method of casing, casing and engine Download PDF

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Publication number
CN117245943A
CN117245943A CN202210656639.XA CN202210656639A CN117245943A CN 117245943 A CN117245943 A CN 117245943A CN 202210656639 A CN202210656639 A CN 202210656639A CN 117245943 A CN117245943 A CN 117245943A
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CN
China
Prior art keywords
preform
manufacturing
reinforcing rib
casing
composite material
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202210656639.XA
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Chinese (zh)
Inventor
张璇
张捷
孔维夷
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Commercial Aircraft Engine Co Ltd
Original Assignee
AECC Commercial Aircraft Engine Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC Commercial Aircraft Engine Co Ltd filed Critical AECC Commercial Aircraft Engine Co Ltd
Priority to CN202210656639.XA priority Critical patent/CN117245943A/en
Publication of CN117245943A publication Critical patent/CN117245943A/en
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
    • B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
    • D03D15/20—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads
    • D03D15/242—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used characterised by the material of the fibres or filaments constituting the yarns or threads inorganic, e.g. basalt
    • D03D15/275—Carbon fibres
    • D—TEXTILES; PAPER
    • D03—WEAVING
    • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
    • D03D25/00—Woven fabrics not otherwise provided for
    • D03D25/005—Three-dimensional woven fabrics
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
    • B29L2031/082—Blades, e.g. for helicopters

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Composite Materials (AREA)
  • Inorganic Chemistry (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

The invention relates to the field of manufacturing of composite material structures, and discloses a composite material structure, a manufacturing method of a casing, the casing and an engine. The composite material structure comprises a body structure and reinforcing ribs, the fiber is used for manufacturing the prefabricated body, the remaining fiber for manufacturing the body prefabricated body is partially separated to be used for manufacturing the reinforcing rib prefabricated body, the prefabricated body formed by the body prefabricated body and the reinforcing rib prefabricated body in an integrated mode is obtained, the manufacturing process of the casing with the reinforcing ribs is simplified, and the structural strength of the interface between the body structure and the reinforcing ribs is improved. The casing comprises a composite material structure, and the manufacturing method of the casing comprises the manufacturing method of the composite material structure. The engine includes the casing.

Description

Composite material structure, manufacturing method of casing, casing and engine
Technical Field
The invention relates to the field of manufacturing of composite material structures, in particular to a manufacturing method of a composite material structure with reinforcing ribs.
Background
There are a large number of blades rotating at high speed in aeroengines and gas turbines, and in the case of foreign object impacts, process defects, etc., the rotating blades may come off. Therefore, the engine casing is required to have good inclusion, so that high-speed and high-energy fragments are ensured not to penetrate the casing, and equipment and personnel are damaged. The presence of a large unbalanced load on the engine rotor after blade flying can cause the engine to vibrate continuously before stopping, during which time the casing is required to maintain a certain structural integrity without disassembly. This has a high requirement for the structural rigidity of the casing.
Meanwhile, the engine case is large in size, and the weight of the engine case can obviously influence the total weight of the engine, so that the efficiency of the engine is further influenced. Carbon fiber composite materials are commonly used for low-temperature end cases in new-generation commercial engines. Patent EP1674244 proposes the use of a triaxial woven preform and a resin-added liquid forming process to manufacture a fan containment casing of equal thickness. Patent EP1674671 proposes a variable thickness fan containment casing, the reinforcement phase of the casing composite core being a braid circumferentially aligned, superimposed in multiple layers, the composite layers being otherwise obtained from a spirally wound braid. Patent US8322971B2 proposes a composite material containing casing, firstly processing a variable thickness fiber preform by a three-dimensional weaving method, then winding the fiber preform on a mandrel in a laminated manner to obtain a casing preform, and then forming the casing by resin liquid.
In the prior art, when manufacturing a composite material structure with reinforcing ribs, a body structure and a prefabricated body of the reinforcing ribs are generally manufactured separately, and then the prefabricated body of the body structure and the prefabricated body of the reinforcing ribs are bonded together, so that the manufacturing process is complex.
Disclosure of Invention
The invention aims to overcome the defect of complex manufacturing process of a composite material structure with reinforcing ribs in the prior art, and provides a composite material structure, a manufacturing method of a casing, the casing and an engine.
The invention solves the technical problems by the following technical scheme:
a method of manufacturing a composite structure comprising a body structure and reinforcing bars, the method comprising the steps of:
s10, manufacturing a prefabricated body of the composite material structure by using fibers;
wherein, the step S10 comprises the following steps:
s11, manufacturing a body preform of the body structure part by using fibers;
s12, manufacturing a reinforcing rib prefabricated body of the reinforcing rib part by using fibers;
in the step S12, after the partial fabrication of the body preform is completed, the fiber for fabricating the body preform is divided into at least two parts, one part is used for continuously fabricating the body preform and the other part is used for fabricating the reinforcing rib preform, so that the body preform and the reinforcing rib preform form a split structure.
In the technical scheme, the fiber for manufacturing the body preform is partially used for manufacturing the reinforcing rib preform, so that the body preform and the reinforcing rib preform are integrally manufactured, namely, in the manufacturing process of the composite material structure preform, the connection of the reinforcing rib and the body structure is completed, and the manufacturing process of the composite material structure is simplified. The body preform and the reinforcing rib preform are formed into a split structure so as to be convenient for separating the body preform from the reinforcing rib preform and facilitating later processing.
Preferably, the method for manufacturing a composite structure further comprises the steps of:
s30, injecting a liquid material into the preform, and then solidifying and forming.
In the technical scheme, liquid material is injected into a preform of the composite material structure and then solidified and molded, so that the composite material structure is obtained. Because the body prefabrication body and the strengthening rib prefabrication body integrated into one piece, pour into liquid material after the resolidification into, structural strength is high in body structure and the interface department of strengthening rib.
Preferably, the method for manufacturing a composite structure further comprises:
s20, correspondingly performing secondary shaping on the preform according to the shape of the composite material structure;
and the step S30 is performed after the step S20.
In the technical scheme, performing secondary shaping on the preform comprises performing secondary shaping on the body preform and/or the reinforcing rib preform. The prefabricated body is subjected to secondary shaping to obtain the preset structural shape of the composite material structure, so that the manufacturing process of the prefabricated body is simplified.
Preferably, in the step S20, the secondary shaping process includes trimming, winding, rotating or folding the preform.
Preferably, the fibers are yarns, the yarns are used for knitting the body preform and the reinforcing rib preform, and in the step S12, after the knitting of the body preform is completed, the yarns used for knitting the body preform are divided into at least two parts, one part is used for continuously knitting the body preform, and the other part is used for knitting the reinforcing rib preform, so that the body preform and the reinforcing rib preform form a fork structure.
Preferably, the method comprises the steps of,
the body preform is of variable thickness, and is manufactured in a yarn increasing and reducing mode;
and/or the reinforcing rib prefabricated body is of a variable thickness, and is manufactured in a yarn increasing and yarn decreasing mode.
In the technical scheme, the thickness of each part of the body prefabricated body and the reinforcing rib prefabricated body is designed, so that the designability of the thickness of the composite material structure is realized, and the designability of the rigidity is realized. The composite material structure which has light structure quality and meets the performance requirements of rigidity, strength and the like is convenient to obtain. The body preform and/or the reinforcing rib preform with variable thickness is manufactured in a yarn increasing and decreasing mode, so that the obtained body preform and/or the reinforcing rib preform has better physical properties such as rigidity and strength.
Preferably, the body preform and the reinforcing rib preform are made of the same raw material.
In the technical scheme, the body prefabricated body and the reinforcing rib prefabricated body are made of the same raw materials, and the liquid forming difficulty of the prefabricated body can be reduced by adopting the mode of homogeneous reinforcement, and the prefabricated body can be formed by one-step solidification, so that the manufacturing links are reduced, and the production efficiency is improved. Meanwhile, the obtained composite material structure has good material uniformity between the body structure and the reinforcing ribs and good physical properties.
Preferably, the body structure is cylindrical; the method of manufacturing a composite structure further comprises:
s20, correspondingly performing secondary shaping on the preform according to the shape of the composite material structure;
in the step S11, the body preform is manufactured into a rectangular flat plate;
in the step S20, the body preform is wound in a cylindrical shape.
Preferably, in the step S20, the number of windings N of the body preform is greater than or equal to 1.
In the technical scheme, in the body structure with the same structural dimension, compared with the winding turns of the body preform, the body preform is thinner and more convenient to wind when the winding turns are multiple turns; meanwhile, the body prefabricated body is thinner, so that the joint is more convenient to lap joint, and the whole circular shape of the body structure is good.
Preferably, the body structure is a variable thickness structure, and the winding number N of the body preform is more than or equal to 2.
In this technical scheme, compare with body prefabrication body only twines one round, the body structure of variable thickness is by body prefabrication body winding multiturn preparation, and the material structure homogeneity of every round is also better, and the physical properties of the body structure that obtains is also better.
Preferably, the body structure is a thick-thickness structure with a middle portion and two thin ends in an axial direction, the body preform is a thick-thickness structure corresponding to the body structure, and the bifurcated portion of the body preform corresponds to the thinner portion of the body preform.
Preferably, the reinforcing rib preform is located at an outermost ring of the body preform, and the step S20 includes:
s201, winding the preform on a core mold;
s202, performing secondary shaping on the reinforcing rib prefabricated body according to the preset structure of the reinforcing rib.
A method of manufacturing a casing comprising a component made of a composite material, the method of manufacturing a casing comprising the method of manufacturing a composite material structure as claimed in any one of the preceding claims.
A casing manufactured according to the manufacturing method of the casing.
A casing comprising a reinforcing rib made of a composite material and a cylindrical body structure, the composite material being used to make a preform of the reinforcing rib and the body structure, the preform of the reinforcing rib being made by separating a portion of the composite material from the composite material of the preform of the body structure.
An engine comprising a casing as claimed in any preceding claim.
The invention has the positive progress effects that:
the fiber used for manufacturing the body preform is partially separated to be used for manufacturing the reinforcing rib preform, so that the body preform and the reinforcing rib preform are integrally manufactured, the reinforcing rib and the body structure are connected in the manufacturing process of the composite material structure preform, and the manufacturing process of the composite material structure is simplified. Through the integrated manufacture of body prefabrication body and strengthening rib prefabrication body, improve the structural strength of body structure and strengthening rib interface department.
Drawings
Fig. 1 is a schematic view of an engine according to embodiment 1 of the present invention;
fig. 2 is a schematic view showing a structure in which a preform according to embodiment 1 of the present invention is wound around a core mold;
FIG. 3 is a schematic view showing the structure of a preform according to embodiment 1 of the present invention;
FIG. 4 is a schematic view of the structure of a body preform according to embodiment 1 of the present invention;
FIG. 5 is a schematic view showing the structure of a reinforcing rib preform according to embodiment 1 of the present invention;
FIG. 6 is a schematic view showing the developed structure of the preform in example 1 after the secondary molding;
FIG. 7 is a schematic view showing the structure of a preform according to embodiment 2 of the present invention;
fig. 8 is a schematic view showing an expanded structure of the preform after secondary molding in embodiment 2 of the present invention.
Reference numerals illustrate:
an engine 1;
a casing 100;
a preform 2;
a body preform 11, a thicker portion 12, a thinner portion 13, a start 14, a finish 15;
the reinforcing rib preform 21, the portion to be trimmed 22, the first portion to be trimmed 221, the second portion to be trimmed 222, the forming portion 23;
a core mold 30;
a longitudinal direction L, a width direction W, and a thickness direction T.
Detailed Description
The invention is further illustrated by means of the following examples, which are not intended to limit the scope of the invention.
The body preform 11 in each embodiment has a rectangular flat structure, and the rectangle is like a rectangle, and may be a rectangle or a cuboid strictly defined in mathematics, or may not be the rectangle; the flat plate structure is similar to a flat plate structure, and can be of equal thickness or of variable thickness. Cylindrical refers to a cylinder shape, which may or may not be a cylinder shape that is strictly defined in mathematics. The words in the left, middle and right directions in the embodiments are merely for convenience of description and do not represent actual situations.
Example 1
Fig. 1 to 6 are schematic structural views of an engine according to embodiment 1 of the present invention, wherein fig. 1 is a schematic structural view of the engine according to embodiment 1, and fig. 2 to 6 are schematic structural views of a preform 2 of a composite material structure according to embodiment 1.
The engine 1 that this embodiment provided is aeroengine, and engine 1's receiver is combined material structure, and the receiver includes body structure and strengthening rib, and wherein body structure is the cylinder, is thick in the middle part in axial direction, and both ends are thin.
The manufacturing method of the casing 100 sequentially includes:
s10, manufacturing a prefabricated body 2 of the machine case by using fibers, wherein the prefabricated body 2 comprises a body prefabricated body 11 and a reinforcing rib prefabricated body 21;
s20, correspondingly performing secondary shaping on the preform 2 according to the shape of the case;
s30, injecting a liquid material into the preform 2 after the secondary shaping, and then solidifying and shaping.
Wherein, the step S10 comprises the following steps:
s11, manufacturing a body preform 11 of a body structure part by using fibers;
s12, manufacturing a reinforcing rib preform 21 of the reinforcing rib part by using fibers.
The step S20 sequentially comprises the following steps:
s201, winding the preform 2 on the mandrel 30;
s202, performing secondary shaping on the reinforcing rib prefabricated body 21 according to a reinforcing rib preset structure.
As shown in fig. 2 and 3, the body preform 11 includes a start end 14 and a finish end 15, and is wound around a mandrel from the start end 14 in step S201, and a longitudinal direction L of the preform corresponds to a circumferential direction of the case.
In this embodiment, the fibers are yarns, which include warp yarns and weft yarns, which are woven using a three-dimensional loom to form a three-dimensional preform 2. Wherein the length direction L of the preform 2 is the warp direction of the weave, and the width direction W is the weft direction of the weave. The yarn adopts carbon fiber. Glass fibers, kevlar fibers, polyimide fibers, silicon carbide fibers, or the like may also be used to weave the preform 2 in other embodiments. In other embodiments, a two-dimensional loom may be used to weave a two-dimensional preform 2.
As shown in fig. 3, the step S10 specifically includes: weaving a section of the initial end 14 of the body preform 11 by using warp yarns and weft yarns on a loom, and then weaving a first circle, a second circle and a third circle corresponding to the body preform 11 in sequence along the length direction L; wherein the stiffener preform 21 is woven at the same time while the outermost turn, i.e., the third turn, of the body preform 11 is woven; after the braiding of the body preform 11 and the rib preform 21 is completed, the excess yarn is trimmed off to form a flat-plate-shaped three-dimensional preform. In other embodiments, the knitting order of the preform 2 may be different from that of the present embodiment, or the outermost ring and the stiffener preform 21 corresponding to the body preform 11 may be knitted first, and then the inner rings such as the second ring and the first ring corresponding to the body preform 11 may be knitted in sequence.
As shown in fig. 3, when the outermost ring corresponding to the body preform 11 is woven, the initial cross section of the outermost ring and the reinforcing rib preform 21 is first woven, and then the outermost ring is continuously woven in the length direction L. In braiding the initial section of the outermost ring and the reinforcing rib preform 21, the steps of:
s101, weaving a thicker part 12 of the body preform 11;
s102, dividing weft yarns on the left side and the right side of the thicker portion 12 into two parts in the thickness direction T according to the thickness design of the body structure, wherein one part of weft yarns is used for continuously weaving the thinner portion 13 of the body preform 11, and the other part of weft yarns is used for weaving the reinforcing rib preform 21, and the reinforcing rib preform 21 and the body preform 11 form a bifurcation structure.
In this embodiment, the body preform 11 is thickened, and when the thicker portion 12 corresponding to the outermost ring is woven, yarns which are originally required to be trimmed are separated for weaving the stiffener preform 21, so that the trimming amount of the yarns is reduced, and the utilization rate of materials is also improved. In the manufacturing process of the prefabricated body 2, the connection of the reinforcing ribs and the body structure is completed, and the manufacturing process of the composite material structure is simplified.
As shown in fig. 3, by separating a yarn of the thicker portion 12 of the knitted body preform 11 into a part for knitting the thinner portion 13 of the body preform 11 and another part for knitting the reinforcing rib preform 21, the body preform 11 and the reinforcing rib preform 21 are integrally formed by yarn connection. Fig. 4 and 5 are views for showing the structures of the body preform 11 and the rib preform 21, and the body preform 11 and the rib preform 21 are actually integrally formed by braiding.
In other embodiments, the yarn may be divided into three or more parts, one part for braiding the body preform 11, one part for braiding the rib preform 21, the other part for trimming off, or the other part for braiding a corresponding preform for the other part of the composite structure. As shown in fig. 2 and 3, in this embodiment, step S202 includes the following steps in order:
s2021, trimming off the part 22 to be trimmed in the reinforcing rib preform 21;
s2022, further, the molding portion 23 in the rib preform 21 is lifted up in a direction perpendicular to the circumferential tangential direction of the body preform 11, and the structure after the preform 2 is unfolded is shown in fig. 6.
In the present embodiment, the portion to be trimmed 22 is trimmed, so that the forming portion 23 is lifted up, and the weight reduction function is also achieved. Winding the preform 2 around the core mold 30, trimming off the portion to be trimmed 22, and lifting up the molding portion 23 belongs to the secondary molding of the preform 2. After the weaving of the preform 2 is completed, the preform 2 is secondarily shaped so as to achieve the purpose of manufacturing the preform 2 into a structure with a preset shape, and the weaving process of the preform 2 is also facilitated to be simplified. In other embodiments, the order of steps S202 and S201 may be interchanged or may be interleaved.
The casing 100 provided in this embodiment has a body structure and a plurality of reinforcing ribs, the body structure is cylindrical, and the plurality of reinforcing ribs are all located on the outer side of the body structure. As shown in fig. 2 and 3, the preform 2 is wound three times around a cylindrical core mold 30, and the molding portion 23 of each bead preform 21 is located outside the outermost ring of the body preform 11.
In other embodiments, in the case of manufacturing another cylindrical composite structure by referring to the manufacturing method of the casing according to the present embodiment, the reinforcing ribs may be provided inside the circular body structure, and may be manufactured by changing the knitting of the preform 2 and changing the structural shape of the core mold 30.
In the present embodiment, the preform 2 is wound around the core mold 30 more than three turns, less than three and a half turns, in order to facilitate the lap process of the starting end 14 and the finishing end 15.
In the present embodiment, the preform 2 is wound three times around the core mold 30. In other embodiments, the winding turn N of the preform on the mandrel 30 may be different from that of the present embodiment, and in the composite material structure with the same shape and size, the more winding turns of the preform 2, that is, the longer the length of the body preform 11, the thinner the thickness of the body preform 11, and the thinner the thickness of the body preform 11 at two broken ends of the starting end 14 and the terminating end 15, so that the easier the overlap joint is, and the whole round shape of the obtained cylindrical body preform 11 is also better.
In this embodiment, the first, second, and third turns of the body preform 11 are identical in each section in the length direction L, that is, the thickness of each turn in the width direction W is identical.
In other embodiments, the body preform 11 may be made into N turns with N being 1 or more by making cylindrical body structures of the same shape and size. When N is more than or equal to 2, the thicknesses of the rings of the body preform 11 can be the same or different; when the thicknesses of all the circles of the body preform 11 are correspondingly the same, all the circles can be woven by adopting the same process, and the process consistency is good; the material uniformity of the body preform 11 after winding is also good, and the mechanical properties of the obtained body structure are also good.
In this embodiment, the step S30 specifically includes:
wrapping the outer surface of the wound preform 2 by using a rigid outer mold or a flexible material, and forming a cavity required by liquid molding with the core mold 30;
heating the wrapped preform 2 and the die by adopting an oven, a press, an autoclave, self-heating or any other proper heating mode, introducing liquid resin into a cavity by using a proper liquid forming process to enable the liquid resin to permeate into the preform 2, curing the resin by adopting heating, pressurizing, vacuumizing or any other proper process method, demoulding the cured casing, and finishing the subsequent processing.
The outer side of the body structure of the casing obtained by the method is provided with the circumferential reinforcing ribs, the body structure prefabricated body 2 and the reinforcing rib prefabricated body 21 are integrally formed through braiding, the connection mode of the body prefabricated body 11 and the reinforcing rib prefabricated body 21 is simple, and the manufacturing process of the prefabricated body 2 is simplified. And the structural strength at the interface of the body structure and the reinforcing rib structure is high.
As shown in fig. 3, in the present embodiment, the thinner portion 13 of the preform 2 and the rib preform 21 corresponding to the left portion in fig. 3 are varied in thickness, and are woven by increasing or decreasing yarns.
By designing the thicknesses of the parts of the body preform 11 and the reinforcing rib preform 21, a reinforcing rib and a body structure with variable thickness are obtained, and designability of the thickness of the composite structure is realized, thereby realizing designability of the rigidity. The prefabricated body 2 corresponding to the part with high rigidity and strength requirements is designed to be thicker, and the prefabricated body 2 corresponding to the part with low rigidity and strength requirements is designed to be thinner, so that the composite material structure with light structure quality and meeting the performance requirements of rigidity and strength and the like is obtained. In other embodiments, the thickness-variable preform 2 structure may be obtained by trimming, folding, or the like, the preform 2. In this embodiment, the thickness-variable preform 2 structure is obtained by increasing or decreasing yarns, so that the manufacturing method of the composite material structure is simple, and the rigidity and strength performance of the finally obtained composite material structure is also good.
In other embodiments, the variable thickness preform 2 may be obtained by trimming the preform 2, folding the preform 2, stitching, folding the preform 2, bonding, or the like, including obtaining the variable thickness body preform 11 and/or the stiffener preform 21.
In this embodiment, the body preform 11 and the rib preform 21 are made of the same material, and the warp and weft are made of the same carbon fiber. The body preform 11 and the reinforcing rib preform 21 are made of the same raw materials, and the liquid forming difficulty of the preform 2 can be reduced by adopting the homogeneous reinforcing mode, and the liquid forming can be performed at one time, so that the manufacturing links are reduced, and the production efficiency is improved. Meanwhile, the obtained composite material structure has good material uniformity between the body structure and the reinforcing ribs and good physical properties.
In other embodiments, the raw materials of the body preform 11 and the bead preform 21 may be partially identical or may be totally different, as long as a composite structure can be produced according to the above-described method.
In this embodiment, a secondary shaping method such as trimming and winding is used for the preform 2, so as to achieve the purpose of making the preform 2 into a structure with a preset shape. In other embodiments, the preform 2 may be subjected to secondary shaping by folding, bending, rotating, and other shaping methods.
In the present embodiment, the body preform 11 uses a plurality of layers of carbon fibers in the longitudinal direction L. In other embodiments, at least two layers of fibers are used in the length direction L of the body preform 11, and each layer of fibers may be the same fibers or different fibers, and if different fibers are used, they may be woven together by a hybrid or mixed weaving method.
Example 2
Fig. 7 and 8 are schematic structural views of a preform 2 of a casing according to embodiment 2 of the present invention.
In this embodiment, the manufacturing method of the casing 100 sequentially includes:
s10, manufacturing a prefabricated body 2 of the casing by using fibers;
s20, correspondingly performing secondary shaping on the preform 2 according to the shape of the case;
s30, injecting a liquid material into the preform 2 after the secondary shaping, and then solidifying and shaping.
In the step S10, when the body preform and the rib preform are woven at the same time, the cross sections of the body preform 11 and the rib preform 21 are woven. The cross sections of the woven body preform 11 and the reinforcing rib preform 21 include the steps of:
s101, weaving a thicker part 12 of the body preform 11;
s102, weaving a thinner part 13 on the left side of a thicker part 12 by a yarn reducing mode, dividing yarns used for weaving the left side of the thinner part 13 into two parts in the thickness direction T, wherein one part of yarns are used for weaving the thinner part 13 on the left side of the thicker part 12, and the other part of yarns are used for weaving a reinforcing rib prefabricated body 21 on the left side of the thicker part 12;
s103, dividing the yarn for knitting the right side of the thick portion 12 into two portions in the thickness direction T, one portion of the yarn for knitting the thin portion 13 on the right side of the thick portion 12 and the other portion of the yarn for knitting the stiffener preform 21 on the right side of the thick portion 12.
The step S20 includes the steps of:
s201, winding the preform 2 on the mandrel 30;
s202, performing secondary shaping on the reinforcing rib prefabricated body 21 according to a reinforcing rib preset structure.
In the present embodiment, the step S202 includes the steps of:
s2021, trimming off the first portion to be trimmed 221;
s2022, trimming off the second part to be trimmed 222, and sewing the forming part 23 shown on the right side of the thicker part 12 on the thinner part 13 of the body preform 11 by using yarn;
s2023, lifting the molding portion 23 to form a structure as shown in fig. 7;
other steps of this embodiment refer to embodiment 1.
As shown in fig. 8, in the present embodiment, the shape, thickness, and knitting pattern of the rib preform 21 are different on the left and right sides. In other embodiments, the shape, thickness, and braiding pattern of the stiffener preform corresponding to the plurality of stiffeners may be the same or different.
In the present embodiment, the portion-to-be-trimmed 22 of the reinforcing-bar preform 21 includes a first portion-to-be-trimmed 221 and a second portion-to-be-trimmed 222. The first part to be trimmed 221 is trimmed to facilitate lifting the molding part 23 for secondary molding, and also has a weight reduction effect. Trimming off the second portion to be trimmed 222 serves to further reduce weight.
In other embodiments, the stiffener preform 21 may be trimmed accordingly, depending on the shape and size of the stiffener.
In the present embodiment, since the second portion to be trimmed 222 is trimmed away, there is no connection between the right-side molding portion 23 and the body preform 11 shown in fig. 7, and the body preform 11 and the right-side molding portion 23 are sewn by using a composite material. In other embodiments, a connection of the reinforcing rib preform 21 and the body preform 11 may be performed by a connection of a composite material such as a glue. In other embodiments, the secondary shaping of the stiffener preform 21 may also be performed by winding, rotating, folding, or the like. In other embodiments, in order to improve the connection strength of the reinforcing rib preform 21 and the body preform 11, a connection manner of a composite material such as stitching, cementing, or the like may be employed to connect the reinforcing rib preform 21 and the body preform 11.
In other embodiments, not only the reinforcing rib preform 21 but also the body preform 11 may be secondarily shaped.
As shown in fig. 7, the thinner portion 13 near both sides of the thicker portion 12 has inclined planes which are provided for a thickness transition between the thicker portion 12 and the thinner portion 13, so that the resulting body structure material is more uniform.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.

Claims (16)

1. A method of manufacturing a composite structure, the composite structure comprising a body structure and reinforcing ribs, the method of manufacturing a composite structure comprising the steps of:
s10, manufacturing a prefabricated body of the composite material structure by using fibers;
wherein, the step S10 comprises the following steps:
s11, manufacturing a body preform of the body structure part by using fibers;
s12, manufacturing a reinforcing rib prefabricated body of the reinforcing rib part by using fibers;
in the step S12, after the partial fabrication of the body preform is completed, the fiber for fabricating the body preform is divided into at least two parts, one part is used for continuously fabricating the body preform and the other part is used for fabricating the reinforcing rib preform, so that the body preform and the reinforcing rib preform form a split structure.
2. A method of manufacturing a composite structure according to claim 1, further comprising the steps of:
s30, injecting a liquid material into the preform, and then solidifying and forming.
3. The method of manufacturing a composite structure of claim 2, further comprising:
s20, correspondingly performing secondary shaping on the preform according to the shape of the composite material structure;
and the step S30 is performed after the step S20.
4. A method of manufacturing a composite structure according to claim 3, wherein in step S20, the secondary shaping process comprises trimming, winding, rotating or folding the preform.
5. The method of manufacturing a composite structure according to claim 1, wherein the fibers are yarns for knitting the body preform and the reinforcing rib preform, and in the step S12, after the partial knitting of the body preform is completed, the yarns for knitting the body preform are divided into at least two parts, one part for continuing the knitting of the body preform and the other part for knitting the reinforcing rib preform, so that the body preform and the reinforcing rib preform are formed into a bifurcated structure.
6. A method of manufacturing a composite structure according to claim 5, wherein,
the body preform is of variable thickness, and is manufactured in a yarn increasing and reducing mode;
and/or the reinforcing rib prefabricated body is of a variable thickness, and is manufactured in a yarn increasing and yarn decreasing mode.
7. The method of manufacturing a composite structure according to claim 1, wherein the body preform and the stiffener preform are made of the same raw material.
8. A method of manufacturing a composite structure according to any one of claims 1 to 7, wherein the body structure is cylindrical; the method of manufacturing a composite structure further comprises:
s20, correspondingly performing secondary shaping on the preform according to the shape of the composite material structure;
in the step S11, the body preform is manufactured into a rectangular flat plate;
in the step S20, the body preform is wound in a cylindrical shape.
9. The method of manufacturing a composite structure according to claim 8, wherein in the step S20, the number of windings N of the body preform is 1 or more.
10. The method of manufacturing a composite structure according to claim 9, wherein the body structure is a variable thickness structure, and the number of windings N of the body preform is greater than or equal to 2.
11. The method of manufacturing a composite structure according to claim 8, wherein the body structure is a thick structure having a middle portion and two ends being thin in an axial direction, the body preform is a thick structure corresponding to the body structure, and a bifurcated portion of the body preform corresponds to a thinner portion of the body preform.
12. The method of manufacturing a composite structure according to claim 9, wherein the reinforcement rib preform is located at an outermost ring of the body preform, and the S20 step includes:
s201, winding the preform on a core mold;
s202, performing secondary shaping on the reinforcing rib prefabricated body according to the preset structure of the reinforcing rib.
13. A method of manufacturing a casing, characterized in that the casing comprises a component made of a composite material, the method of manufacturing a casing comprising the method of manufacturing a composite material structure according to any one of claims 8-12.
14. A casing manufactured according to the manufacturing method of the casing according to claim 13.
15. A casing comprising a reinforcing rib made of a composite material and a cylindrical body structure, the composite material being used to make a preform of the reinforcing rib and the body structure, characterized in that the preform of the reinforcing rib is made by separating a part of the composite material from the composite material of the preform of the body structure.
16. An engine comprising the casing of claim 14 or 15.
CN202210656639.XA 2022-06-10 2022-06-10 Composite material structure, manufacturing method of casing, casing and engine Pending CN117245943A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210656639.XA CN117245943A (en) 2022-06-10 2022-06-10 Composite material structure, manufacturing method of casing, casing and engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210656639.XA CN117245943A (en) 2022-06-10 2022-06-10 Composite material structure, manufacturing method of casing, casing and engine

Publications (1)

Publication Number Publication Date
CN117245943A true CN117245943A (en) 2023-12-19

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210656639.XA Pending CN117245943A (en) 2022-06-10 2022-06-10 Composite material structure, manufacturing method of casing, casing and engine

Country Status (1)

Country Link
CN (1) CN117245943A (en)

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