CN115246235A

CN115246235A - Casing, aircraft engine, manufacturing method of casing and forming die

Info

Publication number: CN115246235A
Application number: CN202110454063.4A
Authority: CN
Inventors: 李曙光; 孔维夷; 张璇; 张建; 胡寿丰; 艾连娜·斯特妮科娃; 许明明
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-04-26
Filing date: 2021-04-26
Publication date: 2022-10-28

Abstract

The disclosure provides a casing, an aircraft engine, a manufacturing method of the casing and a forming die. The casing comprises a main body and a hole arranged on the main body, wherein the main body comprises a composite material layer, the composite material layer comprises a base material and a fiber preform made of fibers, and part of the fibers comprise an avoidance section surrounding the hole. The aircraft engine comprises a casing. The manufacturing method of the casing comprises the following steps: manufacturing a fiber preform by using fibers, wherein the step of enabling the avoidance sections of part of the fibers to pass through the corresponding positions of the holes in a winding manner is included; and manufacturing a composite material layer by adopting the matrix material and the fiber prefabricated body to form the casing. The forming die of machine casket includes: a core mold; a first outer mold; and a second outer mold, wherein the first outer mold includes a first protrusion corresponding to a position of the connection hole to fit a shape of the connection hole, and/or the core mold includes a second protrusion corresponding to a position of the receiving hole to fit a shape of the receiving hole. The mechanical property and the reliability of the casing are improved.

Description

Casing, aircraft engine, manufacturing method of casing and forming die

Technical Field

The disclosure relates to the technical field of manufacturing of aero-engines, in particular to a casing, an aero-engine, a manufacturing method of the casing and a forming die.

Background

A large number of blades rotating at high speed are present in casings of aircraft engines and gas turbines. Under the conditions of external object impact, process defects and the like, the rotating blades can fall off, so that the casing is required to have good containment performance, and high-speed and high-energy blade fragments of the blades are ensured not to penetrate through the casing, so that the equipment and personnel are damaged. The large unbalanced load of the rotor after the blades are flied off can cause the rotor to generate continuous vibration before stopping, and the casing is still required not to be disassembled in the period, so that certain structural integrity is maintained.

Because of the large size of the aircraft engine casing, the weight of the aircraft engine casing has a significant effect on the total weight of the engine, and thus on the efficiency of the engine. For this reason, fiber reinforced composites are commonly used in the low temperature end-boxes of the new generation of commercial aircraft engines. For composite casings, in order to guarantee high mechanical properties and reliability, it is generally desirable that both the axial and circumferential fibers are continuous, i.e.: in the axial direction, the fibers can continuously pass through the casing body from one end flange to the other end flange; in the circumferential direction, the fibers continuously cover the entire circumference.

The casing body is generally cylindrical. Flanges are arranged at two axial ends of the cylindrical structure of the casing body, a plurality of connecting holes are formed in the flanges, and the flanges are fixed on other structures of the aircraft engine through connecting pieces. In addition, openings are also provided in the casing body for the placement of sensors or other functional elements necessary for controlling the aircraft engine. In the related art known to the inventor, the holes on the composite casing are generally processed in the following manner: the casing is integrally formed, and then a hole is formed in the flange or the casing body by removing materials (such as drilling) by machining.

Disclosure of Invention

A first aspect of the present disclosure provides a casing comprising a main body and a bore provided on the main body, the main body comprising a composite layer comprising a matrix material and a fiber preform made of fibers, wherein a portion of the fibers comprise an avoidance segment that bypasses the bore.

According to some embodiments of the disclosure, the body comprises:

a casing body; and

the flanges are positioned at two ends of the casing body;

the hole comprises a connecting hole arranged on the flange and/or a containing hole arranged on the casing body.

According to some embodiments of the disclosure, the casing further comprises a bushing disposed on an inner wall of the bore.

According to some embodiments of the disclosure, the body further comprises a metal layer.

A second aspect of the present disclosure provides an aircraft engine comprising a casing according to the first aspect of the present disclosure.

A third aspect of the present disclosure provides a method of manufacturing a casing according to the first aspect of the present disclosure, including:

manufacturing the fiber preform by using fibers, wherein the avoidance section of part of the fibers bypasses the position corresponding to the hole; and

and manufacturing a composite material layer by adopting the base material and the fiber prefabricated body to form the casing.

According to some embodiments of the present disclosure, the main body includes a casing body and flanges at both ends of the casing body, and the fabricating the fiber preform with fibers includes:

providing the fiber;

providing a forming die, which comprises a core die and a first outer die for providing a die main body;

manufacturing the fiber preform of the casing body on the circumferential outer side of the core mold by using the fibers;

sleeving the first outer die on the outer side of the fiber prefabricated body of the casing body; and

and manufacturing the fiber preform of the flange on the outer side of the axial end face of the first outer die by adopting the fibers.

In accordance with some embodiments of the present disclosure,

the hole including set up in the connecting hole of flange provides forming die still including providing the bellying, the bellying including set up in on the first external mold corresponding to the position of connecting hole and with the first bellying of the shape adaptation of connecting hole, adopt the fibre is in the preparation of the axial terminal surface outside of first external mold the fibre preform of flange includes: passing the avoided segment of a portion of the fibers around the first boss; and/or

The hole including set up in the holding hole of machine casket body, provide forming die still including providing the bellying, the bellying including set up in on the mandrel corresponding to the position of holding hole and with the second bellying of the shape adaptation of holding hole, adopt the fibre is in the circumference outside preparation of mandrel the fibre preform of machine casket body includes: passing a portion of the avoided section of the fibers around the second raised portion.

According to some embodiments of the present disclosure, the fibers include a first fiber, a second fiber, and a third fiber, the first fiber including a body segment, at least a portion of the first fiber further including a reserve segment at both ends of the body segment,

the fiber preform for manufacturing the casing body at the outer side in the circumferential direction of the core mold by using the fibers includes: disposing the first fiber crosswise to the second fiber in the body section; and/or

The fiber preform for manufacturing the flange at the outer side of the axial end face of the first outer die by using the fibers comprises: disposing the first fibers in the reserved section crosswise to the third fibers.

According to some embodiments of the present disclosure, bypassing a portion of the avoided section of the fiber around the first boss comprises: the avoidance sections of two adjacent first fibers in the same layer bypass the first convex parts side by side in the layer.

According to some embodiments of the present disclosure, bypassing a portion of the avoided section of the fiber around the first boss comprises: the avoidance sections of two adjacent first fibers in the same layer bypass the first protruding portion in a stacking manner along the thickness direction of the fiber preform of the flange.

According to some embodiments of the present disclosure, outside the avoidance segment,

disposing the body segment of the first fiber in an axial direction of the mandrel; and/or

Arranging the reserved sections of the first fibers in a radial direction of the first outer mold; and/or

Disposing the second fibers along a circumferential direction of the mandrel; and/or

The third fibers are arranged along the circumferential direction of the first outer die.

According to some embodiments of the present disclosure, providing a forming die further comprises providing a second outer die of the die body; the method for manufacturing the composite material layer by adopting the matrix material and the fiber preform comprises the following steps:

arranging the second outer die on the outer side of the fiber preform of the flange and forming a closed cavity together with the core die and the first outer die, wherein the fiber preform is positioned in the closed cavity;

filling the closed cavity with the matrix material; and

and curing the base material, and demolding to form the composite material layer.

According to some embodiments of the disclosure, the method of manufacturing further comprises:

providing a bushing;

detachably arranging the bushing on the outer wall of the first boss and/or the outer wall of the second boss; and

after the composite material layer is manufactured by adopting the base material and the fiber prefabricated body, the bushing is demoulded together with the composite material layer so that the casing comprises the bushing integrally formed with the composite material layer.

providing a metal layer;

the metal layer is detachably arranged on the circumferential outer side of the core mold; and

after the composite material layer is manufactured by adopting the base material and the fiber prefabricated body, the metal layer is demoulded together with the composite material layer, so that the casing comprises the metal layer integrally formed with the composite material layer.

A fourth aspect of the present disclosure provides a forming mold of a casing according to the first aspect of the present disclosure, including:

a mold body for forming the composite material layer; and

and the protruding part is arranged on the die main body, corresponds to the position of the hole and is matched with the shape of the hole.

In accordance with some embodiments of the present disclosure,

the mold body includes a core mold configured as a mold for making a fiber preform of the casing body, a first outer mold configured as a mold for making a fiber preform of the flange, and a second outer mold configured to form a closed cavity with the core mold and the first outer mold required for filling the base material;

the convex part comprises at least one of a first convex part and a second convex part, wherein the first convex part is arranged on the first outer die corresponding to the position of the connecting hole and matched with the shape of the connecting hole, and the second convex part is arranged on the core die corresponding to the position of the containing hole and matched with the shape of the containing hole.

In accordance with some embodiments of the present disclosure,

the core mould is a combined mould; and/or

The first outer die is a combined die.

Based on the manufacturing method and the forming die of the casing and the casing provided by the disclosure, part of fibers of the casing comprise the avoiding section surrounding the hole, and the fibers with the avoiding section can keep a continuous state at the position corresponding to the hole of the casing, so that the mechanical property of the periphery of the hole of the casing can be improved, the risk of structural failure of the casing is reduced, the reliability of the casing is improved, and the processing efficiency and the processing qualified rate of the casing are improved. The casing is applied to the aero-engine, and accordingly reliability of the aero-engine can be improved.

Other features of the present disclosure and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the disclosure and together with the description serve to explain the disclosure and not to limit the disclosure. In the drawings:

fig. 1 illustrates a cross-sectional structure of a barrel according to some embodiments of the present disclosure.

Figure 2 illustrates the structure of the mandrel of some embodiments of the present disclosure.

FIG. 3 illustrates the use of fibers to make the fiber preform of the case body circumferentially outward of the mandrel in some embodiments of the present disclosure.

Fig. 4 illustrates a state that the first outer mold is sleeved outside the fiber preform of the casing body in some embodiments of the present disclosure.

Fig. 5 illustrates a manner of arranging the reserved section of the first fiber on the first outer mold when the casing is manufactured by the hole-forming method in the related art.

FIG. 6 illustrates the placement of first fibers on a first overmold, in some embodiments of the present disclosure.

FIG. 7 illustrates placement of first fibers on a first overmold, in other embodiments of the present disclosure.

Fig. 8 illustrates a manner in which third fibers are arranged on the first outer mold when the casing is manufactured by using the hole forming method of the related art.

FIG. 9 illustrates the placement of third fibers on the first overmold, in some embodiments of the present disclosure.

Fig. 10 illustrates a state in which the core mold, the first outer mold, and the second outer mold form a closed cavity, and a state in which the fiber preform of the casing is located within the closed cavity, according to some embodiments of the present disclosure.

Detailed Description

The technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure, and it is obvious that the described embodiments are only a part of the embodiments of the present disclosure, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the disclosure, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without making any creative effort, shall fall within the protection scope of the present disclosure.

The relative arrangement of parts and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present disclosure unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as exemplary only and not as limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

In the description of the present disclosure, it should be understood that the terms "first", "second", etc. are used to define the components, and are used only for convenience of distinguishing the corresponding components, and if not otherwise stated, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present disclosure.

In the description of the present disclosure, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are presented only for the convenience of describing and simplifying the disclosure, and in the absence of a contrary indication, these directional terms are not intended to indicate and imply that the device or element being referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the disclosure; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

In the process of implementing the technical solution of the present disclosure, the inventor finds that, in the related art, the following problem may be caused by using a material removal method to machine a hole of a composite casing:

the removal of material causes the continuous fibers within the casing to be broken, and the number of continuous fibers used to provide the force transfer path is reduced, resulting in impaired mechanical properties around the hole. For example, the method of removing the material is adopted to process the connecting holes on the flange, which bear the connecting load, so that the structural failure risk of the casing is obviously increased, and the reliability of the casing is reduced.

Removal of material is often accompanied by additional loads, such as vibration loads during drilling. These additional loads can lead to failure of the inherently weak interlaminar interface in the composite, delamination of the composite, and costly scrapping of the case.

In addition, the composite material with a mixed structure and mixed fibers has richer designability, so that the composite material casing becomes a new development trend. Due to the different processing properties of different types of fibers, if a material removing method is still used for opening holes, the processing quality of the different types of fibers cannot be considered at the same time.

In order to improve the above problem, embodiments of the present disclosure provide a casing, an aircraft engine, a manufacturing method of the casing, and a forming mold.

The aero-engine provided by the embodiment of the disclosure comprises the casing provided by the embodiment of the disclosure, and the advantages of the casing provided by the embodiment of the disclosure are achieved.

Embodiments of the present disclosure provide a case including a body and a bore disposed on the body. The main body includes a composite material layer including a matrix material and a fiber preform made of fibers. Wherein a portion of the fibers include an escape segment around the hole. For example, an avoidance segment L1 as shown in fig. 5, an avoidance segment L2 as shown in fig. 6, and an avoidance segment L3 as shown in fig. 8. The fibers with the avoiding sections can keep a continuous state at the position corresponding to the hole of the casing, so that the mechanical property of the periphery of the hole of the casing is favorably improved, the risk of structural failure of the casing is reduced, the reliability of the casing is improved, and the processing efficiency and the processing qualified rate of the casing are favorably improved. The casing is applied to an aeroengine, and the reliability of the aeroengine can be correspondingly improved.

As shown in fig. 1, the casing is a continuous structure, and the main body includes a casing body 1 and

flanges

2 and 3. The

flanges

2 and 3 are positioned at two ends of the casing body 1. In the case of some embodiments, the holes provided on the body comprise connection holes 21, 31 provided on the

flanges

2, 3 for the connection of the case to other structures of the aircraft engine. In other embodiments, the holes provided in the main body comprise housing holes provided in the casing body 1 for housing sensors or other functional elements required for controlling the aircraft engine. In the above embodiment, the fiber preform includes continuous fibers extending from the flange 2 through the casing body 1 to the flange 3, and the continuous fibers are disposed around the contour of the hole regardless of whether the hole provided in the main body is a connection hole or a receiving hole, and a part of the continuous fibers may include an escape section that bypasses the connection hole, and another part of the continuous fibers may include an escape section that bypasses the receiving hole.

According to design requirements, the composite material layer may include at least one layer of fiber preform, for example, three layers of fiber preforms a, B, C arranged in sequence in the thickness direction of the composite material layer. The thickness of each layer of fiber preform may be different, or the thickness of each layer of fiber preform may be different at different locations. The fiber preform can be made by a weaving process, and can be a two-dimensional woven fiber preform or a three-dimensional woven fiber preform.

As shown in fig. 2 to 10, some embodiments of the present disclosure provide a manufacturing method of a casing, including:

step 1, manufacturing a fiber preform by using fibers, wherein the step comprises the step of enabling an avoidance section of part of the fibers to pass through a position corresponding to a hole.

And 2, manufacturing a composite material layer by adopting the base material and the fiber prefabricated body to form the receiver.

The manufacturing method of the casing provided by the embodiment of the disclosure can enable the avoidance section of part of the fibers to pass through the corresponding position of the hole, and has the advantages of the casing provided by the embodiment of the disclosure. The following describes a method for manufacturing a casing according to an embodiment of the disclosure with reference to fig. 1 to 10.

In some embodiments of the manufacturing method, for a case having a case body 1 and

flanges

2, 3, step 1, the fiber preform is made of fiber, including steps 1.1 to 1.5.

Step 1.1, providing fibers.

According to the design requirements, the continuous fibers required for making the fiber preform are prepared. The material of the fiber can be carbon fiber, glass fiber, aramid fiber, ultra-high molecular weight polyethylene fiber or other suitable fibers. When making a fiber preform, one or more materials of fibers may be used, such as carbon fibers alone, or both carbon fibers and aramid fibers, or a blend of carbon fibers and aramid fibers. The fiber may have various specifications, and when a fiber preform is produced, one or more kinds of fibers of different specifications, for example, carbon fibers of different specifications such as 6K,12K and 24K are used together.

Step 1.2, providing a forming die, including providing a core die 6 and a first outer die 7.

The core mold 6 is used for manufacturing a fiber preform of the casing body 1. As shown in fig. 2, 3 and 10, the core mold 6 may be a cylindrical shape having a shape adapted to the shape of the inner wall of the casing body 1. The outer diameter of the core mold 6 is designed according to the inner diameter of the casing, the length of the core mold 6 is designed according to the distance between the flange 2 and the starting position of the corner of the flange 3, and necessary process errors and curing deformation errors of the composite material are considered during design.

The first outer mould 7 is used for making fibre preforms for the

flanges

2, 3. As shown in fig. 4 and 10, the first outer die 7 may include a cylindrical portion that is form-fitted to the outer wall of the casing body 1 and burring 71, 72 that is form-fitted to the axially inner end faces of the

flanges

2, 3. The inner diameter of the first outer die 7 is designed according to the outer diameter of the casing body 1, the radiuses of the

flanges

71 and 72 are designed according to the radiuses of the

flanges

2 and 3, the distance between the flanges 71 and the end faces of the flanges 72 on the axial outer sides is designed according to the distance between the flanges 2 and the start positions of the corners of the flanges 3, and necessary process errors and curing deformation errors of composite materials are considered during design.

And step 1.3, manufacturing a fiber preform of the casing body 1 on the circumferential outer side of the core mold 6 by using fibers.

In some manufacturing methods of the not-shown embodiments, on the basis that the cassette body 1 is provided with the accommodating hole, in order to facilitate the fiber having the escape section to bypass the position corresponding to the accommodating hole, providing the forming mold further includes providing a protruding portion including second protruding

portions

60a, 60b, 60c provided on the core mold 6 at the position corresponding to the accommodating hole and adapted to the shape of the accommodating hole. The dimensions of the

second protrusions

60a, 60b, 60c are determined according to the dimensions of the receiving holes, and the design takes into consideration the necessary process error and the curing deformation error of the composite material. In step 1.3, the fiber preform for manufacturing the casing body 1 by using the fiber on the outer side of the core mold 6 in the circumferential direction includes: the escape segment of a portion of the fibers is caused to bypass the

second projections

60a, 60b, 60c. When the fiber preform of the casing body 1 is manufactured in the above manner, necessary process errors and curing deformation errors of the composite material are considered.

In some embodiments, the fibers include a first fiber, a second fiber, and a third fiber. The first fiber comprises a body section, at least part of the first fiber further comprises reserved sections located at two ends of the body section, and the body section and the reserved sections are used for manufacturing a fiber preform of the casing body 1 and fiber preforms of the

flanges

2 and 3 respectively. The first, second, and third fibers can each include an avoidance segment.

As shown in fig. 3, in step 1.3, the fiber preform for producing the casing body 1 using the fibers on the outer side in the circumferential direction of the core mold 6 includes: the first fiber is disposed in the body section crosswise to the second fiber. As a concrete form of the fiber preform for making the casing body 1, one or more layers of fiber preforms can be formed by weaving a cylindrical two-dimensional fabric or three-dimensional fabric on the outer side in the circumferential direction of the core mold 6 by a weaving process using the first fibers and the second fibers.

In the above embodiment, the arrangement direction of the first fibers and the second fibers is not exclusive as long as the first fibers and the second fibers can form a crossed fabric structure having a strength satisfying the requirement, and for the first fibers and the second fibers having the avoidance line, it is sufficient that the avoidance line of the first fibers and the avoidance line of the second fibers bypass the second

convex portions

60a, 60b, 60c. For example, the

first fibers

51, 52 may be arranged in the axial direction of the core mold 6 outside the escape section, i.e., outside the position corresponding to the accommodation hole. For another example, the

second fibers

41, 42, 43 may be provided along the circumferential direction of the core mold 6 outside the escape section, that is, outside the position corresponding to the receiving hole.

In some embodiments, as shown in fig. 3, when the first layer fiber preform 10A is produced on the core mold 6, the

first fibers

51, 52 are arranged in the axial direction of the core mold 6 as warp yarns outside the escape section; outside the escape segment, the

second fibers

41, 42, 43 are provided in the circumferential direction of the core mold 6 as weft yarns. The

first fibers

51, 52 are arranged to intersect with the second fibers in a substantial section, and at least a part of the first fibers has a length larger than that of the core mold 6, and the excess portions extending beyond both ends of the core mold 6 in the axial direction are reserved

sections

51a, 52a, 51b, 52b. The lengths of the

reserved sections

51a, 52a and 51b, 52b are determined by the radial dimensions of the

flanges

2, 3, respectively. The reserved sections of the first fibers in the fiber preform 10A are used as a group, and the reserved sections at the two ends of the body section are respectively pulled to the constraint ends F1 and F2 and fixed. The second fibers are disposed between the

second fibers

42 and 43 aligned with the two end edges of the core form 6.

After the fiber preform 10A of the first layer of the casing body 1 is manufactured on the core mold 6, more layers of fiber preforms of the casing body 1, for example, the fiber preforms 10B and 10C of the casing body 1, may be manufactured to the outside in the radial direction of the core mold 6 in sequence according to the above method until the number of layers reaches the design requirement.

Step 1.4, sleeving the first outer die 7 on the outer side of the fiber preform of the casing body 1, as shown in fig. 4.

And step 1.5, manufacturing fiber preforms of the

flanges

2 and 3 on the outer sides of the axial end faces of the first outer die 7 by using fibers.

As shown in fig. 4, in some embodiments, on the basis of the

flanges

2 and 3 being provided with the connecting

holes

21 and 31, in order to facilitate the fibers having the escape sections to bypass the positions corresponding to the connecting

holes

21 and 31, providing the forming mold further includes providing a protruding portion including a first protruding portion 70 provided on the first outer mold 7 corresponding to the positions of the connecting

holes

21 and 31 and adapted to the shapes of the connecting

holes

21 and 31. The size of the first protruding portion 70 is determined according to the size of the connection holes 21 and 31, and the design takes necessary process errors and curing deformation errors of the composite material into consideration. In step 1.5, the fiber preform for manufacturing the

flanges

2 and 3 at the outer side of the axial end face of the first outer die 7 by using fibers comprises: bypassing a portion of the escape segment of the fiber around the first boss 70. When the fiber preforms of the

flanges

2, 3 are manufactured in the above manner, necessary process errors and curing deformation errors of the composite material are taken into consideration.

In some embodiments, the fibers include a first fiber, a second fiber, and a third fiber. The first fibers comprise a body section, at least part of the first fibers further comprise reserved sections located at two ends of the body section, and the body section and the reserved sections are respectively used for manufacturing a fiber preform of the casing body 1 and fiber preforms of the

flanges

2 and 3. The body section of the first fiber, the reserved section of the first fiber, the second fiber, and the third fiber can each include an avoidance section.

In step 1.5, the fiber preform for manufacturing the

flanges

2 and 3 at the outer side of the axial end face of the first outer die 7 by using fibers comprises: the first fibers are arranged in a reserved section crossing the third fibers. As a concrete form of the fiber preform for making the casing body 1, a cylindrical two-dimensional fabric or three-dimensional fabric may be woven on the outer side of the core mold 6 in the circumferential direction by a weaving process using the first fiber and the third fiber to form one or more layers of the fiber preform for the casing body 1.

In the above embodiments, the arrangement direction of the first fibers and the third fibers is not exclusive, as long as the first fibers and the third fibers can form a crossing structure with satisfactory strength. Further, for the first fibers and the third fibers having the escape sections, it is sufficient that the escape sections of the first fibers and the escape sections of the third fibers bypass the first convex portions 70. For example, as shown in fig. 6 and 7, outside the escape sections, that is, outside the positions corresponding to the connection holes, the

reserved sections

53a, 54a, 55a, 56a, 57a, and 58a of the

first fibers

51, 52 may be arranged in the radial direction of the first outer die 7 as warp yarns; for another example, as shown in fig. 9, the

third fibers

90, 91, 92, 93, 94, 95, 96, 97 may be provided as weft yarns in the circumferential direction of the core mold 6 outside the escape segment, that is, outside the position corresponding to the connection hole.

In some embodiments, as shown in fig. 6, 7 and 9, the fixing of the reserve segments of the first fibers of the fiber preform corresponding to the outermost casing body 1 is released from the two restrained ends, respectively, the

reserve segments

53a, 54a, 55a, 56a, 57a and 58a are turned over, and outside the escape segments, the end faces lying against the axially outer sides of the first outer die 7 are arranged in the radial direction of the first outer die 7 as warp yarns; the

third fibers

90, 91, 92, 93, 94, 95, 96, 97 are provided as weft yarns in the circumferential direction of the core mold 6 outside the escape segment.

As shown in fig. 5, if the method of removing material in the related art is used to obtain the hole features such as the connection holes, the

reserved sections

53a, 54a, 55a, 56a, 57a and 58a of the first fibers after being turned over are distributed in a radial shape, and when the connection holes 21 are processed, the

reserved sections

53a, 54a and 55a are broken and the connection holes 56a may be damaged.

The following two ways may be taken in connection with the bypass segment L1 of the first fibers bypassing the first protrusion 70.

In some embodiments, bypassing a bypass segment of a portion of the fibers around the first lobe 70 comprises: the avoidance sections L1 of two adjacent first fibers in the same layer bypass the first protrusions 70 side by side in the layer. For example, as shown in FIG. 6, the

first fibers

53a, 54a, 55a, and 56a in the same layer each include an offset segment, wherein the offset segments of the first fibers 53a are attached to the sides of the first protrusions 70, and the offset segments of each of the

first fibers

53a, 54a, 55a, and 56a are arranged side-by-side around the first protrusions 70 to form a lay pattern similar to concentric circles having different diameters.

In other embodiments, bypassing a bypass segment of a portion of the fibers around the first lobe 70 comprises: the avoiding sections of two adjacent first fibers in the same layer bypass the first convex portions 70 in a stacked manner in the thickness direction of the fiber preform of the

flanges

2, 3. For example, as shown in fig. 7, the

first fibers

53b and 54b in one layer and the

first fibers

55b and 56b in the other layer each include an escape section, wherein the escape sections of the

first fibers

53b, 54b, 55b and 56b are attached to the side of the first protrusions 70, and the first fibers 54b are stacked on the first fibers 53b and the first fibers 56b are stacked on the first fibers 55b in the thickness direction of the fiber preform of the

flanges

2 and 3, forming a laying pattern similar to concentric circles having the same diameter. In order to better control the thickness of the fiber preform of the flange 3, the fiber preform of the cassette body 1 can be provided with a respective yarn reduction R1, R2 in the same direction as the arrangement of the body sections of the first fibers.

As shown in fig. 8, if the method of removing material in the related art is used to obtain the hole features such as the connection holes, the inverted

third fibers

90, 91, 92, 93, 94, 95, 96, 97 are distributed in a concentric circle, and when the connection holes 21 are processed, the

third fibers

93 and 94 are broken, and the

third fibers

92 and 95 may be damaged.

The present disclosure relates to the manner in which the escape segment L3 of the third fiber bypasses the first protrusion 70 as follows: as shown in fig. 9, the

third fibers

90, 91, 92, 93, 94, 95, 96, 97 in the same layer are sequentially disposed outward along the radial direction of the first outer mold 7, wherein the

third fibers

93, 94 have an avoiding section L3, and the avoiding section L3 bypasses the first convex portion 70 from both sides of the first convex portion 70.

The first fibers and the third fibers arranged crosswise are fixed, for example, by pulling, sewing, applying a setting agent, or the like, in such a manner as not to affect the molding of the base material, to form the fiber preform 20C of the first-layer flange 2 and the fiber preform 30C of the flange 3.

After the fiber preform 20C of the first flange 2 and the fiber preform 30C of the flange 3 are produced on the core mold 6, the fixing of the reserved portion of the first fiber corresponding to the fiber preforms of the other respective layers of the casing body 1 can be sequentially released, and the first fiber and the third fiber can be alternately arranged by the above-described method to produce the fiber preforms of the

flanges

2, 3. The third fibers may not be provided in the first fibers of the outermost layer.

According to the manufacturing steps of the fiber preform, the thickness of the fiber preform can be gradually reduced due to the fact that the radius of the first fibers is increased after the first fibers are turned over, and the thickness of the fiber preform can meet the design requirements by adjusting the specification or distribution density of the first fibers and the third fibers, so that the fiber preform of the

flanges

2 and 3 with equal thickness or variable thickness is formed.

In some embodiments, for the case having the case body 1 and the

flanges

2 and 3, the step 2 of manufacturing the composite material layer by using the matrix material and the fiber preform includes steps 2.1 to 2.4.

Step 2.1, providing a forming die, including providing second outer dies 81, 82 of the die body.

The second outer dies 81, 82 are used to form closed cavities with the core die 6 and the first outer die 7 as required for filling the matrix material.

Step 2.2, arranging the second outer dies 81 and 82 on the outer sides of the fiber preforms of the

flanges

2 and 3 and forming closed cavities with the core dies 6 and the first outer dies 7, wherein the fiber preforms are located in the closed cavities, as shown in fig. 10.

The second

outer molds

81, 82 may be formed of a hard metal mold or a flexible material mold.

And 2.3, filling a matrix material such as resin into the closed cavity.

In order to prevent the base material from flowing around the first and

second bosses

70, 60a, 60b, 60c when the base material is filled, further sealing measures may be taken at the positions of the first and

second bosses

70, 60a, 60b, 60c.

And 2.4, curing the base material, and demolding to form the composite material layer.

To facilitate demolding, a mold release agent may be applied to the surfaces of the core mold 6 and the first outer mold 7, particularly the surfaces of the first and

second protrusions

70, 60a, 60b, 60c, before the fiber preform is fabricated.

In some embodiments, not shown, the casing further comprises a liner disposed on an inner wall of the bore to protect the bore.

In some embodiments, the method of manufacturing the casing further includes, in correspondence with a case where an inner wall of the bore of the casing is provided with the bushing: providing a bushing; the bushing is detachably provided to the outer wall of the first boss 70 and/or the outer wall of the

second boss

60a, 60b, 60c. And 2, after the base material and the fiber prefabricated body are adopted to manufacture the composite material layer, the bushing is demoulded together with the composite material layer, so that the casing comprises the bushing integrally formed with the composite material layer.

In some embodiments, not shown, the main body further includes a metal layer, and the metal layer and the composite material layer of the main body form a hybrid structure of the casing, so as to further improve mechanical properties of the casing.

Corresponding to the case where the body of the casing includes a metal layer, in the manufacturing method of some embodiments, the manufacturing method of the casing further includes: providing a metal layer; the metal layer is detachably provided on the outer side in the circumferential direction of the core mold 6. And 2, after the composite material layer is manufactured by adopting the base material and the fiber prefabricated body, the metal layer is demoulded together with the composite material layer so that the casing comprises the metal layer integrally formed with the composite material layer.

As shown in fig. 2 to 10, some embodiments of the present disclosure further provide a forming mold of the aforementioned casing, which, in combination with the manufacturing method of the casing provided by the embodiments of the present disclosure, can be used to manufacture the casing provided by some embodiments of the present disclosure and has the advantages of the casing provided by the embodiments of the present disclosure.

The molding die includes a die main body and a boss. The protruding part is arranged on the die main body corresponding to the position of the hole and matched with the shape of the hole. When the forming die is used for manufacturing the casing of the embodiment of the disclosure, the protruding part can occupy the position corresponding to the hole, and the avoiding section of the fiber can bypass the protruding part to realize the corresponding position of the hole.

In the molding die of some embodiments, the die main body includes the core die 6, the first outer die 7, and the second outer dies 81, 82. The core mold 6 is configured as a mold for making a fiber preform of the casing body 1. The first outer mould 7 is configured as a mould for making fibre preforms for the

flanges

2, 3. The second

outer molds

81, 82 are configured to form closed cavities with the core mold 6 and the first outer mold 7 required for filling the base material. The boss includes at least one of the first boss 70 and the

second bosses

60a, 60b, 60c. Wherein, the first convex part 70 is arranged on the first external mold 7 at the position corresponding to the connecting

holes

21, 31 and is matched with the shapes of the connecting

holes

21, 31;

second protrusions

60a, 60b, 60c are provided on the core mold 6 at positions corresponding to the receiving holes and adapted to the shapes of the receiving holes.

The first projecting portion 70 and the second projecting

portions

60a, 60b, 60c may be fixed to the core mold 6 and the first outer mold 7, respectively, by a detachable connection means such as a screw connection. To facilitate demolding of the corresponding locations of the first and

second bosses

70, 60a, 60b, 60c, the first and

second bosses

70, 60a, 60b, 60c may be provided with a taper.

In the forming die of some not shown embodiments, the outer walls of the first 70 and/or second 60a, 60b, 60c bosses are provided with removable bushings configured to be integrally formed with the composite material layer.

In the forming mold of some not-shown embodiments, a detachable metal layer is provided on the circumferential outer side of the core mold 6, and the metal layer is configured to be integrally formed with the composite material layer.

With regard to the function of the bushing and the metal layer, and the manner of making the bushing and the metal layer transferred from the forming mold to the casing, reference is made to the related description.

According to step 1.2 of the manufacturing method of the casing, in order to facilitate the integral demolding of the formed casing, in some embodiments, the core mold 6 is a combined mold. As shown in fig. 2, the core mold 6 includes removable

core mold members

6a, 6b, and 6c. The shape and number of core members are determined according to the size and structural characteristics of the receiver. The core mold members may be integrally machined or may be assembled after being separately machined. The core 6 may also take other forms of assembly than that shown in figure 2.

According to step 1.2 of the aforementioned manufacturing method of the casing, in order to facilitate the integral demolding of the molded casing, in the molding die of some embodiments, the first outer die 7 is a combined die. As shown in fig. 4, the first overmold 7 includes removable

first overmold parts

7a and 7b. The shape and number of the first outer mold part are determined according to the size and structural characteristics of the casing. The first outer mold parts may be integrally formed or may be assembled after being separately formed. The first overmold 7 may also be assembled differently than in fig. 4.

Finally, it should be noted that: the above examples are intended only to illustrate the technical solutions of the present disclosure and not to limit them; although the present disclosure has been described in detail with reference to preferred embodiments, those of ordinary skill in the art will understand that: modifications to the embodiments of the present disclosure or equivalent substitutions for parts of the technical features can be made, which are intended to be covered by the technical scope of the present disclosure.

Claims

1. A barrel comprising a main body and a bore provided in said main body, said main body comprising a composite layer comprising a matrix material and a fiber preform made of fibers, wherein a portion of said fibers comprise an escape segment bypassing said bore.

2. The barrel of claim 1, wherein said body comprises:

a casing body (1); and

flanges (2, 3) are positioned at two ends of the casing body (1);

the holes comprise connecting holes (21, 31) arranged on the flanges (2, 3) and/or accommodating holes arranged on the casing body (1).

3. A barrel according to claim 1 or 2, further comprising a bushing disposed on an inner wall of said bore.

4. The barrel of claim 1 or 2, wherein said body further comprises a metal layer.

5. An aircraft engine, characterized in that it comprises a casing according to any one of claims 1 to 4.

6. A method of manufacturing a barrel according to any one of claims 1 to 4, comprising:

7. A method of manufacturing a casing according to claim 6, wherein the main body comprises a casing body (1) and flanges (2, 3) at both ends of the casing body (1), and the making of the fiber preform from fibers comprises:

providing the fiber;

providing a forming die, comprising a core die (6) and a first outer die (7) which provide a die body;

manufacturing the fiber preform of the casing body (1) on the circumferential outer side of the core mold (6) by using the fibers;

sleeving the first outer die (7) on the outer side of the fiber prefabricated body of the casing body (1); and

and manufacturing the fiber preforms of the flanges (2, 3) on the outer sides of the axial end faces of the first outer die (7) by adopting the fibers.

8. The method of claim 7, wherein the step of forming the housing includes the step of forming the housing,

the hole including set up in connecting hole (21, 31) of flange (2, 3), provide forming die and still include providing the bellying, the bellying including set up in on first external mold (7) corresponding to the position of connecting hole (21, 31) and with first bellying (70) of the shape adaptation of connecting hole (21, 31), adopt the fibre is in the axial terminal surface outside preparation of first external mold (7) flange (2, 3) the fibre preform includes: bypassing the bypass segment of a portion of the fibers around the first boss (70); and/or

The hole includes a receiving hole provided in the casing body (1), the forming mold further includes a providing protrusion including a second protrusion (60 a, 60b, 60 c) provided on the core mold (6) at a position corresponding to the receiving hole and adapted to the shape of the receiving hole, and the fiber preform for manufacturing the casing body (1) at the outer side of the core mold (6) in the circumferential direction using the fiber includes: bypassing a portion of the avoided section of the fiber around the second boss (60 a, 60b, 60 c).

9. The method of claim 8, wherein the fibers comprise first, second, and third fibers, the first fibers comprising a body segment, at least some of the first fibers further comprising a reserve segment at each end of the body segment,

the fiber preform for manufacturing the casing body (1) at the outer side in the circumferential direction of the core mold (6) using the fibers includes: disposing the first fiber crosswise to the second fiber with the body segment; and/or

The production of the fibre preforms of the flanges (2, 3) outside the axial end faces of the first outer mould (7) using the fibres comprises: disposing the first fibers in the reserved section crosswise to the third fibers.

10. The method of manufacturing a casing according to claim 9, wherein bypassing the escape segment of the portion of the fibers around the first boss (70) comprises: the avoidance sections of two adjacent first fibers in the same layer bypass the first convex part (70) side by side in the layer.

11. The method of manufacturing a casing according to claim 9, wherein bypassing the escape segment of the portion of the fibers around the first boss (70) comprises: the avoidance sections of two adjacent first fibers in the same layer bypass the first protrusions (70) in a stacked manner in the thickness direction of the fiber preform of the flanges (2, 3).

12. The method of manufacturing a barrel according to any one of claims 9 to 11, wherein, outside the bypass section,

arranging the body segment of the first fiber in the axial direction of the mandrel (6); and/or

-arranging said reserve of said first fibres in a radial direction of said first external mold (7); and/or

Arranging the second fibers in a circumferential direction of the core mold (6); and/or

The third fibers are arranged along the circumferential direction of the first outer die (7).

13. A method of manufacturing a barrel according to claim 7, wherein providing a forming die further comprises providing a second outer die (81, 82) of a die body; the method for manufacturing the composite material layer by adopting the matrix material and the fiber preform comprises the following steps:

arranging the second external mold (81, 82) outside the fiber preform of the flange (2, 3) and forming a closed cavity with the core mold (6) and the first external mold (7), wherein the fiber preform is positioned in the closed cavity;

filling the base material into the closed cavity; and

14. The method of manufacturing a casing according to claim 8, further comprising:

providing a bushing;

-removably arranging the bushing on the outer wall of the first boss (70) and/or the outer wall of the second boss (60 a, 60b, 60 c); and

15. The method of manufacturing a casing according to claim 7, further comprising:

providing a metal layer;

the metal layer is detachably arranged on the circumferential outer side of the core mould (6); and

16. A forming die of a casing according to any one of claims 1 to 4, characterized by comprising:

a mold body for forming the composite material layer; and

and the bulge part is arranged on the die main body corresponding to the position of the hole and matched with the shape of the hole.

17. The molding die of claim 16,

the mold body comprises a core mold (6), a first outer mold (7) and second outer molds (81, 82), the core mold (6) is configured as a mold for making fiber preforms of the casing body (1), the first outer mold (7) is configured as a mold for making fiber preforms of the flanges (2, 3), the second outer molds (81, 82) are configured to form closed cavities with the core mold (6) and the first outer mold (7) required for filling the matrix material;

the protruding portions include at least one of first protruding portions (70) and second protruding portions (60 a, 60b, 60 c), wherein the first protruding portions (70) are provided at positions on the first outer die (7) corresponding to the connection holes (21, 31) and adapted to the shapes of the connection holes (21, 31), and the second protruding portions (60 a, 60b, 60 c) are provided at positions on the core die (6) corresponding to the receiving holes and adapted to the shapes of the receiving holes.

18. The molding die according to claim 16 or 17,

the core mould (6) is a combined mould; and/or

The first outer die (7) is a combined die.