CN115256996A - Layering method for cavity area of composite material blade - Google Patents
Layering method for cavity area of composite material blade Download PDFInfo
- Publication number
- CN115256996A CN115256996A CN202210902692.3A CN202210902692A CN115256996A CN 115256996 A CN115256996 A CN 115256996A CN 202210902692 A CN202210902692 A CN 202210902692A CN 115256996 A CN115256996 A CN 115256996A
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- Prior art keywords
- cavity area
- cloth
- composite material
- cylindrical
- cavity
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- 239000002131 composite material Substances 0.000 title claims abstract description 34
- 238000000034 method Methods 0.000 title claims abstract description 19
- 239000004744 fabric Substances 0.000 claims abstract description 72
- 238000005096 rolling process Methods 0.000 claims abstract description 13
- 238000005520 cutting process Methods 0.000 claims abstract description 9
- 239000007787 solid Substances 0.000 claims description 16
- 238000010276 construction Methods 0.000 claims 1
- 230000007547 defect Effects 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
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
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Wind Motors (AREA)
Abstract
The application belongs to the field of design and manufacture of aeroengine blades, and particularly relates to a composite material blade cavity area paving method, which comprises the following steps of 1: cutting the laying cloth into a plurality of rectangular laying cloths, wherein each rectangular laying cloth is provided with a first edge and a second edge which are adjacent to each other, and the length of each first edge is equal to that of the cavity area; step S2: rolling the first edges of the plurality of rectangular layering cloths along the direction of the second edges, so that the plurality of rectangular layering cloths are rolled into a plurality of cylindrical cloth rolls; and step S3: beveling and cutting corners at two ends of the plurality of cylindrical cloth rolls; and step S4: and a plurality of cylindrical cloth rolls are inserted and filled in the cavity area, so that the defects of the composite material stator cavity area are reduced.
Description
Technical Field
The application belongs to the field of design and manufacture of aero-engine blades, and particularly relates to a layer paving method for a composite material blade cavity area.
Background
The stator blade is made of the composite material, so that the low-temperature part of the aero-engine can obtain considerable weight reduction effect and obtain great benefits. The composite stator blade is an I-shaped structure, and is composed of an upper edge plate, a lower edge plate and a blade body, and the composite stator blade is formed by layering mould pressing or autoclave molding. When laying the layer, the blade body and the inner and outer edge plates transfer the cavity area and lay the layer control comparatively important, and the irregular cavity area is laid the layer and is easily produced the defect, reduces blade intensity.
The existing composite material stator blade body and the inner and outer edge plates have no clear requirements on the layer control of the transfer cavity area, so that the problems of low strength of the cavity area, easy defect generation of the cavity area and the like are caused, and the overall strength and the rigidity of the composite material stator blade are reduced.
Disclosure of Invention
In order to solve the above problem, the present application provides a composite material blade cavity area layering method, fills up the cavity area of composite material stator blade, and composite material stator blade includes: the outer edge plate, the inner edge plate and the blade body are connected between the outer edge plate and the inner edge plate; the blade body is provided with a cavity area at the position of connecting the outer edge plate and the inner edge plate, and the cavity area is provided with three wall surfaces;
the layering method for filling the cavity area comprises the following steps:
step S1: cutting the laying cloth into a plurality of rectangular laying cloths, wherein each rectangular laying cloth is provided with a first edge and a second edge which are adjacent to each other, and the length of each first edge is equal to that of the cavity area;
step S2: rolling up the first edges of the plurality of rectangular laying cloths along the direction of the second edge, so that the plurality of rectangular laying cloths are rolled into a plurality of cylindrical cloth rolls;
and step S3: beveling and cutting corners at two ends of the plurality of cylindrical cloth rolls;
and step S4: and inserting a plurality of cylindrical cloth rolls to fill the cavity area.
Preferably, the plurality of cylinders filling the cavity area include a large cylinder cloth roll and a plurality of small cylinder cloth rolls, and the diameter of the large cylinder cloth roll is larger than that of the small cylinder cloth roll.
Preferably, the side surface of the large cylinder cloth roll is tangent to three wall surfaces of the cavity area, and the plurality of small cylinder cloth rolls are respectively positioned at the joint of two adjacent wall surfaces of the cavity area.
Preferably, the radius r of the large cylinder cloth roll satisfies the following formula: more than 0.25a and r are less than or equal to 0.28a, wherein a is the width of the minimum wall surface of the cavity area.
Preferably, the radius of a plurality of said cylindrical rolls is different.
Preferably, a plurality of the cylindrical cloth rolls are of a solid structure.
Preferably, the method for rolling the cylindrical cloth into the solid structure comprises the following steps: determining the size of a single rectangular laying cloth, rolling the rectangular laying cloth with the determined size into a solid cylindrical cloth roll, and obtaining the maximum diameter of the solid cylindrical cloth roll; and rolling the rectangular laminated cloth with the same size into a solid cylindrical cloth roll by taking the maximum diameter as a standard.
The advantages of the present application include:
1. the filling plumpness of the cavity area of the stator blade made of the composite material is improved;
2. the filling consistency of the cavity area of the composite stator blade is improved;
3. the strength and the rigidity of the cavity area of the composite stator blade are improved;
4. the strength and rigidity consistency of the cavity area of the composite stator blade is improved;
5. the defects of the composite material stator cavity area are reduced;
6. the integral strength and rigidity of the composite stator blade are improved;
7. the consistency of the overall strength and the rigidity of the composite stator blade is improved.
Drawings
FIG. 1 is a schematic view of a composite stator blade of the present application;
FIG. 2 isbase:Sub>A cross-sectional view A-A of the composite stator blade of FIG. 1;
FIG. 3 is a cylindrical roll of fabric having a chamfered corner;
fig. 4 is a schematic cross-sectional view of a cylindrical roll of fabric filled into a cavity area.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
As shown in fig. 1 and fig. 2, the present application provides a method for laying layers in a cavity region of a composite material stator blade, which fills the cavity region of the composite material stator blade, and the composite material stator blade includes: the outer edge plate, the inner edge plate 2 and the blade body 5 connecting the outer edge plate 1 and the inner edge plate 2; the blade body 5 is provided with a cavity area at the position of connecting the outer edge plate 1 and the inner edge plate 2, and the cavity area is provided with three wall surfaces;
the paving method for filling the cavity area comprises the following steps:
example 1:
step S1: cutting the laying cloth into multi-phase rectangular laying cloth with the same size, namely that the adjacent first edge and second edge of each rectangular laying cloth are respectively the same, wherein the length of the first edge is equal to that of the cavity area;
step S2: rolling up the first edges of the plurality of rectangular laying cloths along the direction of the second edges to roll the plurality of rectangular laying cloths into a plurality of identical cylindrical cloth rolls, wherein the cylindrical cloth rolls are solid, and the method for determining the plurality of cylindrical cloth rolls to be solid comprises the following steps: determining the size of a single rectangular laying cloth, rolling the rectangular laying cloth with the determined size into a solid cylindrical cloth roll, and obtaining the maximum diameter of the solid cylindrical cloth roll; taking the maximum diameter as a standard, and rolling the rectangular layering cloth with the same size into a solid cylindrical cloth roll;
and step S3: the two ends of the plurality of cylindrical cloth rolls are obliquely cut, and the narrow openings are prevented from being deformed due to the obliquely cut corners at the two ends of the cavity;
and step S4: and inserting a plurality of cylindrical cloth rolls to fill the cavity area.
The second embodiment:
step S1: cutting the laying cloth into a plurality of rectangular laying cloths, wherein each rectangular laying cloth is provided with a first edge and a second edge which are adjacent to each other, and the length of each first edge is equal to that of the cavity area;
step S2: rolling up the first edges of the plurality of rectangular laying cloths along the direction of the second edge, so that the plurality of rectangular laying cloths are rolled into a plurality of cylindrical cloth rolls; the plurality of cylindrical cloth rolls are solid;
and step S3: beveling and cutting corners at two ends of the plurality of cylindrical cloth rolls;
and step S4: and inserting a plurality of cylindrical cloth rolls to fill the cavity area.
Furthermore, the plurality of cylinders filling the cavity area comprise a large cylinder cloth roll and three small cylinder cloth rolls; the side surface of the large cylinder cloth roll is tangent with three wall surfaces of the cavity area, the three small cylinder cloth rolls are respectively positioned at the joint of two adjacent wall surfaces of the cavity area, each small cylinder cloth roll is respectively tangent with two adjacent wall surfaces of the cavity area and the cylindrical surface of the large cylinder cloth roll,
in order to better realize the tangency of the side surfaces of the large cylinder cloth roll and the three wall surfaces of the cavity area, the radius r of the large cylinder cloth roll meets the following formula: more than 0.25a and r are less than or equal to 0.28a, wherein a is the width of the minimum wall surface of the cavity area, and can be the width of the wall surface formed by the outer edge plate 1 or the inner edge plate 2 of the cavity area.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A layer paving method for a cavity area of a composite material stator blade fills a cavity area of the composite material stator blade, and the composite material stator blade comprises the following steps: the outer edge plate, the inner edge plate (2) and the blade body (5) connected between the outer edge plate (1) and the inner edge plate (2); the blade body (5) is provided with a cavity area at the position of connecting the outer edge plate (1) and the inner edge plate (2), and the cavity area is provided with three wall surfaces;
the paving method for filling the cavity area is characterized by comprising the following steps:
step S1: cutting the laying cloth into a plurality of rectangular laying cloths, wherein each rectangular laying cloth is provided with a first edge and a second edge which are adjacent to each other, and the length of each first edge is equal to that of the cavity area;
step S2: rolling up the first edges of the plurality of rectangular laying cloths along the direction of the second edge, so that the plurality of rectangular laying cloths are rolled into a plurality of cylindrical cloth rolls;
and step S3: beveling and cutting corners at two ends of the plurality of cylindrical cloth rolls;
and step S4: a plurality of cylindrical rolls of cloth are inserted to fill the cavity.
2. A composite material blade cavity layup method as defined in claim 1, wherein the plurality of cylinders filling the cavity area comprises a large cylinder roll and a plurality of small cylinder rolls, the diameter of the large cylinder roll being greater than the diameter of the small cylinder rolls.
3. A composite material blade cavity layup method as defined in claim 2, wherein the lateral surface of the large cylindrical fabric roll is tangent to three wall surfaces of the cavity, and the plurality of small cylindrical fabric rolls are respectively located at the joint of two adjacent wall surfaces of the cavity.
4. A composite material blade cavity area layup method as claimed in claim 1, wherein the radius r of the large cylinder cloth roll satisfies the following formula: more than 0.25a and r are less than or equal to 0.28a, wherein a is the width of the minimum wall surface of the cavity area.
5. A composite material blade cavity area layup method as claimed in claim 1, wherein a plurality of said cylindrical fabric rolls differ in radius.
6. A composite material blade cavity area layup method as claimed in claim 5, wherein a plurality of said cylindrical fabric rolls are of solid construction.
7. A method of laying up a composite blade cavity region as claimed in claim 6, wherein the method of rolling up the cylindrical cloth into a solid structure is: determining the size of a single rectangular laying cloth, rolling the rectangular laying cloth with the determined size into a solid cylindrical cloth roll, and obtaining the maximum diameter of the solid cylindrical cloth roll; and rolling the rectangular laminated cloth with the same size into a solid cylindrical cloth roll by taking the maximum diameter as a standard.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210902692.3A CN115256996A (en) | 2022-07-29 | 2022-07-29 | Layering method for cavity area of composite material blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210902692.3A CN115256996A (en) | 2022-07-29 | 2022-07-29 | Layering method for cavity area of composite material blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115256996A true CN115256996A (en) | 2022-11-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210902692.3A Pending CN115256996A (en) | 2022-07-29 | 2022-07-29 | Layering method for cavity area of composite material blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115256996A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101445663A (en) * | 2008-11-12 | 2009-06-03 | 中国航空工业第一集团公司北京航空制造工程研究所 | Filler and filling method for composite material structure void area |
| US20120074265A1 (en) * | 2009-06-11 | 2012-03-29 | Saab Ab | Nano-reinforced radius filler for an aircraft structure and a method of producing an aircraft structure comprising such filler |
| CN102529113A (en) * | 2011-12-27 | 2012-07-04 | 成都飞机工业（集团）有限责任公司 | Filling method of corner gaps of composite material component |
| CN104690982A (en) * | 2013-12-10 | 2015-06-10 | 惠阳航空螺旋桨有限责任公司 | Composite stator blade of engine and preparation method of composite stator blade |
| RU2599661C1 (en) * | 2015-07-28 | 2016-10-10 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method of making composite stiffness element |
| CN111070724A (en) * | 2019-11-20 | 2020-04-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Integral forming method and tool for composite material U-shaped stringer wallboard |
| CN111590917A (en) * | 2020-05-20 | 2020-08-28 | 航天海鹰(镇江)特种材料有限公司 | Filling method of variable-section R-angle gap carbon twisted yarns |
-
2022
- 2022-07-29 CN CN202210902692.3A patent/CN115256996A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101445663A (en) * | 2008-11-12 | 2009-06-03 | 中国航空工业第一集团公司北京航空制造工程研究所 | Filler and filling method for composite material structure void area |
| US20120074265A1 (en) * | 2009-06-11 | 2012-03-29 | Saab Ab | Nano-reinforced radius filler for an aircraft structure and a method of producing an aircraft structure comprising such filler |
| CN102529113A (en) * | 2011-12-27 | 2012-07-04 | 成都飞机工业（集团）有限责任公司 | Filling method of corner gaps of composite material component |
| CN104690982A (en) * | 2013-12-10 | 2015-06-10 | 惠阳航空螺旋桨有限责任公司 | Composite stator blade of engine and preparation method of composite stator blade |
| RU2599661C1 (en) * | 2015-07-28 | 2016-10-10 | Акционерное общество "Обнинское научно-производственное предприятие "Технология" им. А.Г. Ромашина" | Method of making composite stiffness element |
| CN111070724A (en) * | 2019-11-20 | 2020-04-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Integral forming method and tool for composite material U-shaped stringer wallboard |
| CN111590917A (en) * | 2020-05-20 | 2020-08-28 | 航天海鹰(镇江)特种材料有限公司 | Filling method of variable-section R-angle gap carbon twisted yarns |
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