CN114542202A - Layer layout design structure of composite material closed annular casing - Google Patents
Layer layout design structure of composite material closed annular casing Download PDFInfo
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- CN114542202A CN114542202A CN202210133396.1A CN202210133396A CN114542202A CN 114542202 A CN114542202 A CN 114542202A CN 202210133396 A CN202210133396 A CN 202210133396A CN 114542202 A CN114542202 A CN 114542202A
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- 239000002131 composite material Substances 0.000 title claims abstract description 36
- 238000013461 design Methods 0.000 title claims abstract description 29
- 230000007704 transition Effects 0.000 claims abstract description 42
- 230000008719 thickening Effects 0.000 claims abstract description 31
- 239000000463 material Substances 0.000 claims abstract description 7
- 238000000265 homogenisation Methods 0.000 claims 1
- 239000002184 metal Substances 0.000 abstract description 13
- 230000005540 biological transmission Effects 0.000 abstract description 7
- 230000007423 decrease Effects 0.000 abstract 2
- 239000010410 layer Substances 0.000 description 68
- 238000000034 method Methods 0.000 description 11
- 238000004519 manufacturing process Methods 0.000 description 9
- 230000007547 defect Effects 0.000 description 7
- 230000003247 decreasing effect Effects 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 238000003754 machining Methods 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 238000003892 spreading Methods 0.000 description 3
- 230000007480 spreading Effects 0.000 description 3
- 238000005520 cutting process Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 229920001721 polyimide Polymers 0.000 description 2
- 239000009719 polyimide resin Substances 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The application belongs to the field of aero-engine structure design and strength analysis, and relates to a composite material closed annular casing layering design structure which comprises a cylinder body, a transition region, a thickening region, an R region and a flanging which are sequentially connected, wherein the cylinder body, the transition region, the thickening region, the R region and the flanging are uniformly arranged in an integrated manner, namely the casing is continuously layered from the cylinder body to the flanging on the whole, a metal mounting edge and a rivet connecting structure of the metal mounting edge are omitted, and the load transmission efficiency of the casing is improved; the problem of incongruity of thermal deformation of different materials in the case in a working state is solved; the thickness of the layer of the flange is the same as that of the layer of the thickening area, the layer between the thickening area and the transition area decreases from the thickening area to the transition area in a stepped manner, and the layer between the transition area and the barrel decreases from the transition area to the barrel in a stepped manner, so that the state of the thickened layer is extended to the barrel of the casing.
Description
Technical Field
The application belongs to the field of aero-engine structure design and strength analysis, and particularly relates to a composite material closed annular casing laying layer design structure.
Background
The composite material has been applied to aerospace product design due to the characteristics of light weight, excellent material performance, strong designability and the like. Due to installation, use and maintenance requirements of aircraft engine components, and limitations in molding processes, machining methods and the like of composite materials, only a portion of the casings may be made of composite materials. Therefore, in the design of the aeroengine casing, not only the structural design of the casing body is required, but also the connection design of the composite material casing and other metal casings is required, and the connection structure has the characteristics of large load transmission, complex load form and high-temperature environment bearing.
The engine case mainly bears two types of internal pressure loads and mechanical loads and needs to meet the requirements of high strength and rigidity, so that the aircraft engine case is designed to adopt a carbon fiber reinforced polyimide resin matrix composite material and meet the requirement of high temperature resistance. As shown in fig. 1, the connection structure of the casing is: the metal mounting edge is fixedly connected with the composite material annular casing by rivets, and the metal mounting edge of the composite material casing is connected with other casings by bolts and nuts so as to achieve the purposes of engine flow passage design and load transfer among the casings.
Under the high-temperature working condition, the annular casing connecting structure made of the polyimide resin-based composite material has the following defects:
1) the load transfer part and the rivet connection result in a large number of holes formed at the edge of the composite material casing, the problem of local stress concentration at the periphery of the holes exists, and the manufacturing defects such as layering and the like are easily generated during the hole forming of the casing;
2) the metal mounting edge is riveted with the composite material casing, so that the problem of incongruity of thermal deformation generated inside the component in a high-temperature working environment is solved;
3) the composite material large-diameter annular thin-wall casing has insufficient rigidity and is easy to deform in use;
4) the connecting structure between the casings is complex, the load transmission efficiency is low, and the load form is complex;
5) the large-scale forged metal mounting edges and numerous rivets are adopted, so that the number of parts of the casing is increased, on one hand, the weight of the casing is increased, and the advantage of light weight of the composite material is seriously weakened; on the other hand, the machining process and the machining cost of the casing are increased, and the machining efficiency is low.
The bearing capacity of the composite material casing is reduced by a large number of densely-arranged holes at the edge of the composite material casing, the problems of concentrated stress at the hole edge, inconsistent thermal deformation, manufacturing defects and the like.
Therefore, how to improve the bearing capacity of the casing is a problem to be solved.
Disclosure of Invention
The application aims at providing a composite material closed annular casing laying layer design structure to solve the problem that in the prior art, the bearing capacity of a casing is poor due to the problems of stress concentration, thermal deformation incongruity and the like caused by the fact that a composite material casing is connected with a metal mounting edge through rivets.
The technical scheme of the application is as follows: a layer layout structure of a composite material closed annular casing comprises a cylinder body, a transition area, a thickening area, an R area and a flanging which are sequentially connected; the barrel, the transition area, the thickening area, the R area and the flanging are arranged in a unified manner, the layer spreading thickness of the flanging is the same as that of the thickening area, the layer spreading between the thickening area and the transition area is gradually decreased from the thickening area to the transition area, the layer spreading between the transition area and the barrel is gradually decreased from the transition area to the barrel, and the flanging is connected with the adjacent case through bolts.
Preferably, in the layer structure of the barrel, the transition region, the thickening region, the R region and the flanging, one side of the circumferential 90-degree layer close to the flanging is spliced into a plus or minus 45-degree layer, and a gap is formed between the 90-degree layer and the plus or minus 45-degree layer at the same level.
Preferably, the splicing positions of the circumferential 90-degree laminates are alternately switched between the transition region and the thickened region every certain number of layers from outside to inside.
Preferably, the R region is filled with partial layers of layers from outside to inside every certain number of layers.
Preferably, the ply ratio of the barrel is 0 °: plus or minus 45 degrees: 90 ° -1: 2: 2.
preferably, the layering proportion of the thickening area, the R area and the flanging is 0 degree: plus or minus 45 degrees: 90 ° -1: 4: 2.
preferably, the fillet R of the laminated structure of the R region is 1+0.1n, and n is the number of fillet layers.
The composite material closed annular casing layering design structure comprises a cylinder body, a transition area, a thickening area, an R area and a flanging which are sequentially connected, wherein the cylinder body, the transition area, the thickening area, the R area and the flanging are uniformly arranged, namely the casing is continuously layered from the cylinder body to the flanging on the whole, a metal mounting edge and a rivet connection structure of the metal mounting edge are eliminated, a load transmission path is simplified, and the load transmission efficiency of the casing is improved; the problem of incongruity of thermal deformation of different materials in the case in a working state is solved; the thickness of the layer of the flange is the same as that of the layer of the thickening area, the layer between the thickening area and the transition area is decreased in a step mode from the thickening area to the transition area, and the layer between the transition area and the barrel is decreased in a step mode from the transition area to the barrel, so that the state of the thickened layer is extended to the barrel of the engine case.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of a background art structure;
FIG. 2 is an enlarged view of the case connection structure and the integral flange connection structure according to the present application;
FIG. 3 is a cross-sectional structural view of a casing ply of the present application;
FIG. 4 is a schematic diagram of a fracture structure of a single-layer circumferential ply at a flanging in the prior art;
FIG. 5 is a schematic view of a flanged ply structure after splicing according to the present application;
FIG. 6 is a schematic cross-sectional view of an R-zone ply interlaminar fill design of the present application.
1. A barrel; 2. a transition zone; 3. a thickened region; 4. a region R; 5. and (5) flanging.
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 drawings in the embodiments of the present application.
A composite material closed annular casing layering design structure is shown in figures 2 and 3 and comprises a cylinder body 1, a transition area 2, a thickening area 3, an R area 4 and a flanging 5 which are connected in sequence. The length directions of the barrel 1, the transition region 2 and the thickening region 3 are all arranged along the axial direction of the casing, and the length direction of the flanging 5 is arranged along the radial direction of the casing; one side of the R area 4 close to the inner part of the casing is provided with a 90-degree corner which connects the thickening area 3 and the flanging 5, and the R area 4 is of an arc concave structure at the outer side of the casing and forms a fillet of a laminating structure in the concave part. The flanges 5 are connected with adjacent metal casings through bolts.
The barrel 1, the transition area 2, the thickening area 3, the R area 4 and the flanging 5 are arranged in a unified manner, namely, the casing is continuously layered from the barrel 1 to the flanging 5 on the whole, a metal mounting edge and a rivet connecting structure of the metal mounting edge are omitted, a load transmission path is simplified, and the load transmission efficiency of the casing is improved. The problem of incongruity of thermal deformation of different materials in the case in a working state is solved; meanwhile, edge hole making is not needed, the structural form is simplified, the problem of stress concentration does not exist in the casing, manufacturing defects such as layering and the like cannot be generated, and the bearing capacity is greatly improved.
Meanwhile, the integral rigidity of the casing is improved, the deformation resistance is improved, the production cost is reduced due to the reduction of the number of parts, the production period is shortened, and the weight reduction advantage of the composite material is fully exerted.
Because the thickness of turn-ups 5 is greater than the thickness of barrel 1, in order to satisfy the layer demand of each part, consider the influence of layer decrement to intensity simultaneously, set up thickening district 3 and transition district 2, the layer thickness of turn-ups 5 is the same with the layer thickness of layering of thickening district 3, the layer between thickening district 3 and transition district 2 is from thickening district 3 to transition district 2 ladder decrement, the layer between transition district 2 and barrel 1 is from transition district 2 to barrel 1 ladder decrement, thereby extend the thickening layer state to machine casket barrel 1, when this layer design method guarantees each part intensity demand of machine casket, compromise the weight reduction design demand of engine part, will lay the layer number of piles minimizing.
When the step decreasing of the layers at the thickening region 3, the transition region 2 and the barrel 1 is carried out, the +/-45-degree layers are preferably removed, but the layers at other angles can be removed.
The ply processing manufacture preferably employs an autoclave molding process.
Preferably, as shown in fig. 4, when the casing is laid by using the unidirectional composite material, since the circumferential 90 ° ply may greatly change in the local size of the flange 5, a fan-shaped fracture gap is generated, multiple filling is required to achieve the whole-layer laying, the operation is cumbersome and inefficient, and manufacturing defects caused by cutting generally occur, so in order to more effectively prevent the fracture, the specific operation is as follows:
as shown in FIG. 5, in the layer structure of the barrel 1, the transition region 2, the thickening region 3, the R region 4 and the flanging 5, one side of the circumferential 90-degree layer close to the flanging 5 is spliced into a +/-45-degree layer, a gap is formed between the 90-degree layer and the +/-45-degree layer at the same level, and stress concentration at the gap can be avoided due to the arrangement of the gap. By adopting the splicing design, on one hand, the problem of breakage of the layer at the flanging 5 can be solved, and the manufacturing defects caused by cutting and filling of the layer at the flanging 5 are effectively reduced; on the other hand, the composite material can meet the local bearing requirement, the equivalent isotropic design requirement of the R region 4 and the flanging 5 laminated structure is met, the design target of the composite material distribution as required is realized, and the material use efficiency is improved.
Based on the principle of equilibrium design, the splicing paving layer selects a paving layer based on the middle plane symmetrical depth.
As shown in fig. 6, the splicing positions of the circumferential 90 ° plies are preferably staggered and switched between the transition zone 2 and the thickened zone 3 every certain number of layers from outside to inside. The number of layers that separate can be 1 layer, 2 layers or other, take 2 layers as an example, when 2 layers splice in transition district 2 positions on the top, 2 adjacent layers splice in 3 positions in the thickened area down, 2 adjacent layers return to 2 positions in the transition district again and splice, so relapse, until all splices are accomplished, because the concatenation position of laying the layer staggers, can effectively reduce the influence of concatenation interface to the receiver bearing capacity, guarantee the intensity of receiver.
Preferably, the R-zone 4 is filled with partial plies at intervals of a certain number of plies from the outside to the inside.
The connection of the engine case needs to ensure the continuity and smoothness of an air flow channel, the R area 4 laying layer design is realized by adopting a method of filling local laying layers among layers, the right-angle shape of a flow channel of the engine case can be effectively ensured, for the composite material with poor resin matrix fluidity, the method utilizes the structure to lay and solidify the composite material, the layers are tightly adhered and compacted, gaps among the laying layers are reduced, the purpose of reducing air and volatile substances in the curing process of the engine case is achieved, meanwhile, the problem that the relative sliding of the laying layers generates solidification stress when the material expands with heat and contracts with cold in the curing process of the R area 4 laying layer is solved, and the method is an effective method for controlling manufacturing defects in the forming process of the resin matrix composite material closed annular case flanging 5 and the R area 4.
The number of plies for a partial ply spacing may be 1, 2, or other number of plies.
Preferably, the ply ratio of the cylinder 1 is 0 °: plus or minus 45 degrees: 90 ° -1: 2: 2. the layering proportion of the R area 4 and the flanging 5 is 0 degree: plus or minus 45 degrees: 90 ° -1: 4: 2. according to the characteristics of the engine case, enough axial 90-degree layers are designed at the position of the cylinder body 1, the R area 4 and the flanging 5 are thickened to achieve a smaller isotropic target, therefore, the R area 4 and the flanging 5 are thickened by adopting +/-45-degree layers, in order to prevent the influence of layer decreasing on the strength, the thickened layer state is extended to the thickened area 3, namely, the layer proportion of the thickened area 3 is the same as that of the R area 4 and the flanging 5.
Preferably, the fillet R of the laminated structure of the R region 4 is 1+0.1n (mm), where n is the number of fillet layers. That is, the more the number of the paving layers, the more the inner fillet of the laminated structure is increased linearly to ensure the close compaction between the paving layers of the R area 4.
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. The utility model provides a layer design structure is spread to combined material closed ring shape machine casket which characterized in that: comprises a cylinder body (1), a transition area (2), a thickening area (3), an R area (4) and a flanging (5) which are connected in sequence; barrel (1), transition district (2), thickened area (3), R district (4) and turn-ups (5) homogenization setting, turn-ups (5) spread the layer thickness the same with the layer thickness that spreads of thickened area (3), the layer between thickened area (3) and transition district (2) is from thickened area (3) to transition district (2) ladder degressive, the layer between transition district (2) and barrel (1) is spread from transition district (2) to barrel (1) ladder degressive, pass through bolted connection between turn-ups (5) and the adjacent machine casket.
2. A composite closed loop casing layup design structure as claimed in claim 1, wherein: in the layer structure of barrel (1), transition district (2), thickened area (3), R district (4) and turn-ups (5), splice the 90 layers of circumference for 45 layers near one side of turn-ups (5) to 90 layers and 45 layers at the same level have the clearance between the layer.
3. A composite closed loop casing layup design structure as claimed in claim 2, wherein: and the splicing positions of the circumferential 90-degree layers are alternately switched between the transition area (2) and the thickening area (3) at intervals of a certain number of layers from outside to inside.
4. A composite closed loop casing layup design structure as claimed in claim 1, wherein: and local layers are filled among the layers of the R area from outside to inside at certain layer intervals.
5. The composite material closed loop casing ply design structure of claim 1, wherein: the layering proportion of the cylinder (1) is 0 degree: plus or minus 45 degrees: 90 ° -1: 2: 2.
6. a composite closed loop casing layup design structure as claimed in claim 1, wherein: the layering proportion of the thickening area (3), the R area (4) and the flanging (5) is 0 degree: plus or minus 45 degrees: 90 ° -1: 4: 2.
7. a composite closed loop casing layup design structure as claimed in claim 1, wherein: and the inner fillet R of the laminated structure of the R region (4) is 1+0.1n, and n is the number of fillet paving layers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210133396.1A CN114542202A (en) | 2022-02-11 | 2022-02-11 | Layer layout design structure of composite material closed annular casing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210133396.1A CN114542202A (en) | 2022-02-11 | 2022-02-11 | Layer layout design structure of composite material closed annular casing |
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| CN114542202A true CN114542202A (en) | 2022-05-27 |
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| CN202210133396.1A Pending CN114542202A (en) | 2022-02-11 | 2022-02-11 | Layer layout design structure of composite material closed annular casing |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110821583A (en) * | 2019-12-05 | 2020-02-21 | 中国航发四川燃气涡轮研究院 | Edge connecting structure of cartridge receiver barrel and cartridge receiver |
| CN112182800A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Cylindrical case laying layer design method of resin-based composite material |
| CN112199796A (en) * | 2020-10-16 | 2021-01-08 | 中国航发四川燃气涡轮研究院 | Method for designing composite material culvert casing layering |
-
2022
- 2022-02-11 CN CN202210133396.1A patent/CN114542202A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110821583A (en) * | 2019-12-05 | 2020-02-21 | 中国航发四川燃气涡轮研究院 | Edge connecting structure of cartridge receiver barrel and cartridge receiver |
| CN112182800A (en) * | 2020-09-18 | 2021-01-05 | 中国航发四川燃气涡轮研究院 | Cylindrical case laying layer design method of resin-based composite material |
| CN112199796A (en) * | 2020-10-16 | 2021-01-08 | 中国航发四川燃气涡轮研究院 | Method for designing composite material culvert casing layering |
Non-Patent Citations (1)
| Title |
|---|
| 张瑜 等: "复合材料机匣整体翻边拼接结构设计与试验验证", 《纤维复合材料》, no. 2, 15 May 2019 (2019-05-15), pages 34 - 38 * |
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