CN101723086A - Containing ring of aircraft engine fan made of fiber-reinforced composite material - Google Patents
Containing ring of aircraft engine fan made of fiber-reinforced composite material Download PDFInfo
- Publication number
- CN101723086A CN101723086A CN200910153836A CN200910153836A CN101723086A CN 101723086 A CN101723086 A CN 101723086A CN 200910153836 A CN200910153836 A CN 200910153836A CN 200910153836 A CN200910153836 A CN 200910153836A CN 101723086 A CN101723086 A CN 101723086A
- Authority
- CN
- China
- Prior art keywords
- ring
- fiber
- fibrous bundle
- epoxy resin
- reinforced composite
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
Abstract
The invention discloses a containing ring of an aircraft engine fan made of a fiber-reinforced composite material. The containing ring is made of the fiber-reinforced resin-based composite material; and the fibers are flat fiber bundle two-dimensional braided tubes which are arranged around the axes of the containing ring along the length direction. The containing ring has the advantages of high fragment impacting resistant layering capacity, excellent fragment containing capacity, light weight, low cost and the like. The invention also discloses a method for preparing the containing ring; and the method is simple to operate, and adopts the conventional weaving equipment and curing equipment without special equipment.
Description
Technical field
The present invention relates to the aero-engine casing technical field, be specifically related to a kind of fiber reinforced composite aerial engine fan and contain ring.
Background technology
The non-inclusive accident of aero-engine can cause fatal crass's serious airplane crash.If the dangerous fragment of high speed high energy penetrates casing and flies out, can wound cabin, fuel tank, hydraulic tubing and the electrical control circuit etc. of aircraft, cause cabin decompression, fuel tank to leak on fire, aircraft and control secondary such as malfunctioning and destroy, seriously jeopardize flight safety.As seen the containing ability of aero-engine casing is vital for the safety of aircraft, and is therefore in the ascendant always about the research of high strength and High Performance casing.
Aero-engine contains casing and comprises the containing ring that is positioned at engine blower blade periphery, and the performance requriements that contains ring with respect to the containing casing at other position of driving engine is higher.It is material that early stage containing ring generally adopts steel or aluminum alloy/titanium alloy with high-strength structure, has intensity height, good toughness, the advantage that protection effect is good.But the density of steel, aluminum alloy, titanium alloy material and quality are all very big, and the containing circumpolar of making is for heavy, are twined to strengthen by quality and structure is light and handy, the containing ability is strong high strength fibre gradually and contain ring and full composite material and contain ring and replace.
Existing fiber twines to strengthen to contain to encircle to be made by fiber reinforced epoxy resin, be generally and outside the inner liner metal layer, twine high strength fibre silk or the fibrous bundle that resin soaks, the fiber yarn of the good resin of pre-preg or fibrous bundle are twined the back curing molding by the winding direction layering that designs get final product.Its winding process can adopt craft or fiber winding machine to carry out, but this method winding process complexity, the winding number of turns is many, lost time, and also owing to directly twine by fiber yarn or fibrous bundle, the fiber interlaminar strength is low, the containing performance of the casing that weakened.Simultaneously, during winding in the fibrage between fiber and basal body interface than being easier to occur defective and pore, technology is difficult to control.
Full composite material containing ring adopts the laminated mode of woven cloth intersection winding or the mode of 3 D weaving to prepare usually.Compare with the containing ring that laminated mode prepares, the 3 D weaving full composite material contains ring and has higher shearing strength value and fracture ductility at thickness direction, reduced delamination failure to containing the weakening of ring containing ability, but need to adopt the 3 D stereo weaving technology, its job operation is loaded down with trivial details, production cycle is long, and cost is very high.Traditional woven cloth is twined reinforced composite materials and is contained ring, though easily manufactured, because it is discontinuous to contain the fiber at ring two ends, under high speed impact load, contain rim bearing and be subjected to the fiber of tensile stress to be easy to occur relaxing, cause structure slack and undisciplined, reduce and contain performance.The damage mode of 3 D weaving full composite material structure and failure criteria still do not have accurate cognition and assurance at present, at the containing ring that bears high speed impact load, have to adopt the load design measure of big nargin, the application that this has also hindered the 3 D weaving full composite material to contain ring.
A kind of fibre-reinforced metal/ceramic laminated composite containment casing is disclosed in the Chinese patent 200610113400.9, it has at least one metal level/fibrage/ceramic layer sandwich construction, and wherein sandwich construction is at high temperature to connect technology, powder sintering process, active metal brazing technology with metal level, fibrage and ceramic layer weld together by the activity casting.This contains casing hardness height, good toughness, in light weight, has and protects the ability that the high speed object impacts preferably, can be widely used in various types of turbofan aero-engine on.But such casing complicated process of preparation, cost is higher, and the perfect criterion of strength of the mechanical property of metal/ceramic layer shortage, needs to a great extent to adopt bigger load nargin and safety factor during the design casing, has restricted its application.
The production method of same with thermosetting compound material product commonly used mainly comprises hand pasting forming at present, hand is stuck with paste flexible bag moulding, injection molding, winding, pultrusion, resin transfer molding (RTM), the resin glued membrane soaks into moulding (RFI) and prepreg/Autoclave forming and compression molding etc.Wherein prepreg/autoclave forming process is owing to easy construction, and less demanding to workman's technical ability, production efficiency height, goods have higher density, and performance is more stable and intensity is good, has obtained using widely; Its step generally comprises: design, twine paving by construction process requirement on mould according to the shop layer, then carry out bag, so that its inside is in vacuum state and produces negative pressure, the final pore-solids ratio of eliminating in the forming process, after bag is finished, send in the autoclave, under 80～180 ℃ temperature, under 2～5 atmospheric pressure, it is curing molding that whole solidification process continues 6～8h.
Summary of the invention
The invention provides a kind of fiber reinforced composite aerial engine fan and contain ring, its fibrous bundle control of two-dimensional braided pipe with the pressing of continuous winding is a skeleton, be aided with resin solidification and be prepared from, have intensity height, good toughness, in light weight and impact resistance bed resolution and the ability of containing excellent characteristics.
A kind of fiber reinforced composite aerial engine fan contains ring, this containing ring is made by fiber-reinforced resin matrix compound material, the fibrous bundle control of two-dimensional braided pipe of described fiber for flattening, the wrapped along its length appearance annulate shaft of the described fibrous bundle control of two-dimensional braided pipe heart is arranged.
Described fibrous bundle control of two-dimensional braided pipe is to adopt existing two-dimensional two to form to braiding or the braiding of two-dimentional three-dimensional, the two dimension two that the field routine is weaved in utilization to knit unit with warp with parallel is woven into existing braiding decorative pattern tissue or utilize the two-dimentional three-dimensional knit unit of weaving the field routine that first direction line, second direction line and three-dimensional line are woven into existing braiding decorative pattern tissue gets final product (as shown in Figure 3), wherein, described warp, parallel, first direction line, second direction line or three-dimensional line are fibrous bundle.
Described braiding decorative pattern tissue can be selected plain weave, satin weave or twill etc. for use.
The width of the fibrous bundle control of two-dimensional braided pipe of described pressing is determined according to the width of existing containing ring.
The fibrous bundle of described fibrous bundle preferred high strength, high tenacity, such fibrous bundle tensile strength generally reaches more than the 1300MPa, and strength-to-density ratio reaches 6 * 10
4M～12 * 10
4M, specific modulus is up to 5 * 10
6M～16 * 10
6M when improving intensity, has alleviated weight, greatly as carbon fiber bundle (T300, T700) or aramid fiber bundle (Kevlar, polyisophthaloyl metaphenylene diamide fibre are that aramid fiber 1313, Fanglun 1414 are Fanglun l414) etc.
The epoxy resin of premium properties such as described resin preferably has cure shrinkage low (only 1%～3%), cohesiveness is good, mechanical characteristics is good, electrical isolation and withstanding corrosion, good stability, can select polyfunctional epoxy resin (as MDA epoxy resin, novolac epoxy etc.), bisphenol A type epoxy resin, glycidyl ester type epoxy resin or cycloaliphatic epoxy resin etc. for use, for example commercially available prod commonly used in the aeronautical material: a kind of among epoxy resin 4211, epoxy resin 5208, the epoxy resin 914C etc.
Described fiber reinforced composite aerial engine fan contains the preparation method of ring, may further comprise the steps:
(1) adopts existing control of two-dimensional braided technology that fibrous bundle is woven into fibrous bundle control of two-dimensional braided pipe, fibrous bundle control of two-dimensional braided pipe is flattened form fibrous bundle braiding strap then;
(2) with above-mentioned fibrous bundle braiding strap, behind the good resin of pre-preg, successively twine paving on mould, through the hot-press solidifying moulding, obtain containing ring, perhaps above-mentioned fibrous bundle braiding strap is successively twined paving on mould, after the hot-press solidifying moulding, obtain containing ring at perfusion resin.
Adopt the fiber tube that flattens not to be prone to the slip and the buckling phenomenon of fiber in operating process, the conformability of machine direction and collimation can be controlled preferably.In addition, under the effect of autoclave pressure, can realize higher fiber content, obtain the containing ring of higher mechanical property.
Described hot-press solidifying moulding can be adopted existing solidification of hot-press tank moulding, its technological parameter is identical with the curing molding parameter of existing general composite material, be parameters such as solidification temperature (comprising warming and cooling rate, thermostat temperature and solidification temperature), forming pressure (comprising pressure applying moment, pressure size) and heat-insulation pressure keeping time, determine according to selected epoxy resin and tow material.General under 80～180 ℃ temperature, under 2～5 atmospheric pressure, whole solidification process continues 6～8h and is cured moulding.The consumption of epoxy resin is specifically determined according to the condition of hot-press solidifying and the FAW value of fiber (being the fiber unit weight) and RC value (being resin impregnation ratio), the weight of general epoxy resin is 20%～30% of fibre weight, in order to improve the containing performance, should improve fiber content and density as far as possible.
Described mould comprises the core that is used to twine fibrous bundle braiding strap, the two ends of core radially extend to form stop member, this stop member will be wrapped in the edge of the fibrous bundle braiding strap on the core and fix, and prevent that fibrous bundle braiding strap from skidding off in the process of twining.Operation can be served as stop member at the two ends of core mounting flange for convenience.
The shape of the containing ring that described core prepares as required determines, can adopt the cross section is the containing ring that the tubular core of circle or similar round (as ellipse etc.) prepares the rule annular, is used for the engine blower periphery more; Also can adopt the core of taper, truncated cone-shaped to prepare the containing ring of irregular annular, be used for the outer culvert casing that driving engine contains casing (be driving engine contain in the casing other positions of containing ring contain casings) etc. more except fan.
Engine blower of the present invention contains ring can also contain ring as the cold junction of aero-engine, as the casing of low-pressure compressor, the casing of high-pressure compressor etc.
The present invention has the following advantages:
Compare with traditional containing ring, fiber reinforced composite aerial engine fan of the present invention contains ring and adopts strength-to-density ratio and the very high high strength composite fiber reinforcement of specific modulus, has the advantage that weight is lighter, the containing ability is stronger.Wheel disc 1/2 burst test and numerical simulation result of calculation show, under identical containing Capability Requirement (the 1/2 wheel disc fragment that high speed centrifugation flies out after promptly containing explosion), the present invention is contained weight saving that the chain rate metallic material contains ring more than 70%, twines than traditional fiber to strengthen the weight saving more than 25% of containing ring.
Simultaneously, fiber reinforced composite aerial engine fan containing ring of the present invention has very strong impact resistance bed resolution.This has benefited from the continuity of braided fiber bundle, and containing ring of the present invention is under the high speed impact loading, and improvement value, particularly axial tensile-strength can improve more than 40% greatly to bear circumferential and axial tensile stress ability.And the thin walled fiber bundle control of two-dimensional braided pipe that flattens is an interlayer unit with bilayer, also has certain continuity at interlayer, and anti-bed resolution increases.
It is simple to operate that the preparation method of ring is contained in the present invention, adopts existing conventional fabric manufacture equipment and curing apparatus to get final product, and need not special specialized equipment, and cost is low.The manufacturing interior diameter contains ring at 1.5 meters～2.0 meters aerial engine fan, and its cost has only 1/10th of titanium alloy casing, and traditional fibre is twined and strengthened about 1/2nd of containing ring.
Description of drawings
Fig. 1 contains the structural representation of ring for the present invention;
Fig. 2 is the structural representation of mould of the present invention;
Fig. 3～Fig. 9 contains the braiding decorative pattern organizational structure scheme drawing of the fiber tube that flattens in the ring for the present invention.
The specific embodiment
As shown in Figure 2, mould of the present invention comprises the cylindric core 1 that is used to twine fibrous bundle braiding strap 4, and the two ends of core 1 are equipped with flange 2 and flange 3, by lock screw 5 locking flange 2 and flanges 3, be equipped with top wire hole on flange 2 and the flange 3, place lock screw when being used for the demoulding.
The aerial engine fan of manufacturing in 150 big aircraft utilizations of level contains the experimental test containing ring that the about 12 times ratio of ring is dwindled.Adopt two-dimentional three-dimensional braider, the T300 carbon fiber bundle of selecting the 12k of cost performance optimum (promptly containing 12000 carbon fiber wires in a carbon fiber bundle) in the market for use is as first direction line, second direction line and three-dimensional line, according to two-dimentional three-dimensional weaving manner as shown in Figure 3, knitting out semi-perimeter is the fibrous bundle two dimension three-dimensional braided tube of 72mm.Then fibrous bundle two dimension three-dimensional braided tube is flattened into the double braid strap that width is 72mm, effectively avoid cutting to introduce the fibrous bundle cross break.
Behind above-mentioned double braid cloth preimpregnation high-toughness epoxy resin 5208 matrixes, at external diameter winding shaping on the cylindrical mold of φ 150mm.Adopt the solidification of hot-press tank moulding: the mould of winding product is put the sealing poly-bag, and being evacuated to the relative vacuum degree is-0.096MPa to advance in the autoclave then, feed steam, be warming up to 85 ℃, constant temperature 30 minutes, continue to be warming up to 125 ℃, be incubated 2 hours, discharge the bubble in the winding product gap; Lower the temperature with the rate of temperature fall of 0.5 ℃ of per minute then, pressurization 0.4MPa when being cooled to 90 ℃, release when being cooled to 60 ℃, whole solidification process is 7 hours.The demoulding behind hot-press solidifying can obtain internal diameter φ 150mm, height 72mm, and the containing ring test spare of thickness 12mm, its structure is as shown in Figure 1.
Above-mentioned containing ring test spare is carried out wheel disc 1/2 burst test, observed data numerical simulation result of calculation shows, under identical containing Capability Requirement (the 1/2 wheel disc fragment that high speed centrifugation flies out after promptly containing explosion), the weight saving 40% that strengthens the containing ring is twined in the weight saving 90% that above-mentioned containing ring test spare contains ring than metallic material than traditional fiber.
Above-mentioned containing ring test spare is carried out Mechanics Performance Testing under the high speed impact loading, the result shows, above-mentioned containing ring test spare bears circumferential and axial tensile stress ability and contains ring and traditional fiber winding enhancing containing ring apparently higher than metallic material, its axial tensile-strength contains ring than metallic material and has improved 83%, twines enhancing containing ring than traditional fiber and has improved 70%; Its anti-bed resolution contains ring than metallic material and has improved 85%, twines enhancing containing ring than traditional fiber and has improved 66%.
The aerial engine fan of manufacturing in 150 big aircraft utilizations of level contains the experimental test containing ring that the about 12 times ratio of ring is dwindled.Adopt two dimension two to braider, the 12k high-strength carbon fiber bundle T700 that selects cost performance optimum in the market for use is as warp and parallel, be woven into the tabby fibrous bundle two dimension two that has as shown in Figure 5 to braided tube, fibrous bundle two dimension two is 72mm to the semi-perimeter of braided tube, fiberoptic fiber Shu Erwei two is flattened to braided tube form the fibrous bundle braiding strap that width is 72mm.
Behind above-mentioned double braid cloth preimpregnation high-toughness epoxy resin 4211 matrixes, at external diameter winding shaping on the cylindrical mold of φ 150mm.Adopt the solidification of hot-press tank moulding: the mould of winding product is put the sealing poly-bag, and being evacuated to the relative vacuum degree is-0.09MPa to advance in the autoclave then, feed steam, be warming up to 90 ℃, constant temperature 30 minutes, continue to be warming up to 130 ℃, be incubated 2 hours, discharge the bubble in the winding product gap; Lower the temperature with the rate of temperature fall of 0.8 ℃ of per minute then, pressurization 0.35MPa when being cooled to 95 ℃, release when being cooled to 60 ℃, whole solidification process is 6 hours.The demoulding behind hot-press solidifying can obtain internal diameter φ 150mm, height 72mm, and the containing ring test spare of thickness 12mm, its structure is as shown in Figure 1.
Above-mentioned containing ring test spare is carried out wheel disc 1/2 burst test, observed data numerical simulation result of calculation shows, under identical containing Capability Requirement (the 1/2 wheel disc fragment that high speed centrifugation flies out after promptly containing explosion), the weight saving 42% that strengthens the containing ring is twined in the weight saving 85% that above-mentioned containing ring test spare contains ring than metallic material than traditional fiber.
Above-mentioned containing ring test spare is carried out Mechanics Performance Testing under the high speed impact loading, the result shows, above-mentioned containing ring test spare bears circumferential and axial tensile stress ability and contains ring and traditional fiber winding enhancing containing ring apparently higher than metallic material, its axial tensile-strength contains ring than metallic material and has improved 75%, twines enhancing containing ring than traditional fiber and has improved 60%; Its anti-bed resolution contains ring than metallic material and has improved 78%, twines enhancing containing ring than traditional fiber and has improved 45%.
The aerial engine fan of manufacturing 150 big aircraft utilizations of level contains ring.Adopt existing two-dimentional three-dimensional knitting skill, as first direction line, second direction line and three-dimensional line, according to two-dimentional three-dimensional weaving manner as shown in Figure 3, knitting out semi-perimeter is the fibrous bundle two dimension three-dimensional braided tube of 320mm with Kevlar49.Then fibrous bundle two dimension three-dimensional braided tube is flattened into the double braid strap that width is 320mm.
The epoxy resin 914C that the preimpregnation of above-mentioned double braid cloth is produced by Ciba company is that φ 1800mm, width are winding shaping on the cylindrical shape core 1 of 320mm at external diameter, and the thickness of winding is 30mm.Adopt the solidification of hot-press tank moulding: the mould of winding product is put the sealing poly-bag, being evacuated to the relative vacuum degree is-0.095MPa, advance in the autoclave then, feed steam, be warming up to 100 ℃, constant temperature 35 minutes continues to be warming up to 140 ℃, be incubated 2 hours, discharge the bubble in the winding product gap; Lower the temperature with the rate of temperature fall of 0.9 ℃ of per minute then, pressurization 0.2MPa when being cooled to 80 ℃, release when being cooled to 60 ℃, whole solidification process is 8 hours.The demoulding behind hot-press solidifying can obtain internal diameter φ 1800mm, height 320mm, and the containing ring test spare of thickness 30mm, its structure is as shown in Figure 1.
Above-mentioned containing ring test spare is carried out wheel disc 1/2 burst test, observed data numerical simulation result of calculation shows, under identical containing Capability Requirement (the 1/2 wheel disc fragment that high speed centrifugation flies out after promptly containing explosion), the weight saving 45% that strengthens the containing ring is twined in the weight saving 88% that above-mentioned containing ring test spare contains ring than metallic material than traditional fiber.
Above-mentioned containing ring test spare is carried out Mechanics Performance Testing under the high speed impact loading, the result shows, above-mentioned containing ring test spare bears circumferential and axial tensile stress ability and contains ring and traditional fiber winding enhancing containing ring apparently higher than metallic material, its axial tensile-strength contains ring than metallic material and has improved 79%, twines enhancing containing ring than traditional fiber and has improved 80%; Its anti-bed resolution contains ring than metallic material and has improved 76%, twines enhancing containing ring than traditional fiber and has improved 75%.
Claims (8)
1. a fiber reinforced composite aerial engine fan contains ring, this containing ring is made by fiber-reinforced resin matrix compound material, it is characterized in that: the fibrous bundle control of two-dimensional braided pipe of described fiber for flattening, the wrapped along its length appearance annulate shaft of the described fibrous bundle control of two-dimensional braided pipe heart is arranged.
2. fiber reinforced composite aerial engine fan as claimed in claim 1 contains ring, it is characterized in that: described fibrous bundle control of two-dimensional braided pipe adopts two dimension two to braiding or the braiding of two-dimentional three-dimensional.
3. fiber reinforced composite aerial engine fan as claimed in claim 1 contains ring, and it is characterized in that: described fibrous bundle is carbon fiber bundle or aramid fiber bundle.
4. fiber reinforced composite aerial engine fan as claimed in claim 1 contains ring, and it is characterized in that: described resin is an epoxy resin.
5. fiber reinforced composite aerial engine fan as claimed in claim 4 contains ring, and it is characterized in that: described epoxy resin is polyfunctional epoxy resin, bisphenol A type epoxy resin, glycidyl ester type epoxy resin or cycloaliphatic epoxy resin.
6. fiber reinforced composite aerial engine fan as claimed in claim 5 contains ring, it is characterized in that: described epoxy resin is a kind of among MDA epoxy resin, novolac epoxy, epoxy resin 4211, epoxy resin 5208, the epoxy resin 914C.
7. contain the preparation method of ring as each described fiber reinforced composite aerial engine fan of claim 1～6, may further comprise the steps:
(1) fibrous bundle is woven into fibrous bundle control of two-dimensional braided pipe, fibrous bundle control of two-dimensional braided pipe is flattened form fibrous bundle braiding strap then;
(2) with above-mentioned fibrous bundle braiding strap, behind the good resin of pre-preg, successively twine paving on mould, through the hot-press solidifying moulding, obtain containing ring, perhaps above-mentioned fibrous bundle braiding strap is successively twined paving on mould, after the hot-press solidifying moulding, obtain containing ring at perfusion resin.
8. fiber reinforced composite aerial engine fan as claimed in claim 7 contains the preparation method of ring, it is characterized in that: described mould comprises the core that is used to twine fibrous bundle braiding strap, and the two ends of core radially extend to form the stop member that is used for fixing fibrous bundle woven cloth belt edge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910153836A CN101723086A (en) | 2009-11-16 | 2009-11-16 | Containing ring of aircraft engine fan made of fiber-reinforced composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910153836A CN101723086A (en) | 2009-11-16 | 2009-11-16 | Containing ring of aircraft engine fan made of fiber-reinforced composite material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101723086A true CN101723086A (en) | 2010-06-09 |
Family
ID=42444781
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910153836A Pending CN101723086A (en) | 2009-11-16 | 2009-11-16 | Containing ring of aircraft engine fan made of fiber-reinforced composite material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101723086A (en) |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102700149A (en) * | 2012-05-23 | 2012-10-03 | 德阳协同达塑胶电料有限公司 | Method and mould for manufacturing insulation box |
| CN103407171A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integral forming method for sewing enhanced cross connector made of fiber reinforced resin matrix composite |
| CN103639101A (en) * | 2013-11-15 | 2014-03-19 | 西安航空动力股份有限公司 | Method for coating abradable coating of composite containing ring of aircraft engine |
| CN104386129A (en) * | 2014-10-22 | 2015-03-04 | 徐东 | Automobile radiator crossbeam made of fiber reinforced composite material and manufacturing method thereof |
| CN106671443A (en) * | 2015-11-05 | 2017-05-17 | 空中巴士运营有限公司 | Method, forming and injection tool for manufacturing aperture surrounding frame for aircraft fuselage, and the frame obtained thereof |
| CN107139507A (en) * | 2017-06-15 | 2017-09-08 | 西安交通大学 | A kind of high crash-worthiness cylindrical structure forming method of composite |
| CN110849738A (en) * | 2019-12-09 | 2020-02-28 | 湖南崇德工业科技有限公司 | Fiber reinforced composite material winding mandrel, winding tool and stretching tool |
| CN111051585A (en) * | 2017-08-30 | 2020-04-21 | 赛峰飞机发动机公司 | Woven fiber structure for forming shell preform |
| CN111267373A (en) * | 2018-12-05 | 2020-06-12 | 湖南易净环保科技有限公司 | Method for producing damp-proof insulating pipe for live working by squeezing, drawing and winding |
| CN111912619A (en) * | 2020-06-01 | 2020-11-10 | 浙江海骆航空科技有限公司 | Axial containment test device and method for turbine engine exhaust casing |
| CN112412878A (en) * | 2020-09-30 | 2021-02-26 | 航天材料及工艺研究所 | Capturing type ballistic impact resistant composite material fan casing and manufacturing method thereof |
| CN112848378A (en) * | 2020-12-26 | 2021-05-28 | 吉林大学 | Fiber reinforced composite blade material with bionic structure and preparation method thereof |
| CN113290966A (en) * | 2021-05-21 | 2021-08-24 | 山东中恒景新碳纤维科技发展有限公司 | Multilayer woven fiber composite material and application thereof, ski vehicle shell and preparation method thereof |
| CN113524719A (en) * | 2021-06-28 | 2021-10-22 | 武汉理工大学 | Curing self-tightening heat treatment integrated process for metal lining fiber winding gas storage cylinder |
| CN113858650A (en) * | 2020-06-30 | 2021-12-31 | 中国航发商用航空发动机有限责任公司 | Method for manufacturing composite annular parts |
| CN114643725A (en) * | 2020-12-21 | 2022-06-21 | 中国航发商用航空发动机有限责任公司 | Manufacturing method of composite casing and composite casing |
| CN115352102A (en) * | 2022-07-29 | 2022-11-18 | 中国航发沈阳发动机研究所 | Manufacturing method of composite material containing ring for engine case and engine case |
| CN116001307A (en) * | 2021-10-22 | 2023-04-25 | 中国科学院宁波材料技术与工程研究所 | Composite plate spring and preparation method thereof |
| CN114643725B (en) * | 2020-12-21 | 2024-04-26 | 中国航发商用航空发动机有限责任公司 | Manufacturing method of composite casing and composite casing |
-
2009
- 2009-11-16 CN CN200910153836A patent/CN101723086A/en active Pending
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102700149A (en) * | 2012-05-23 | 2012-10-03 | 德阳协同达塑胶电料有限公司 | Method and mould for manufacturing insulation box |
| CN102700149B (en) * | 2012-05-23 | 2014-04-02 | 德阳协同达塑胶电料有限公司 | Method and mould for manufacturing insulation box |
| CN103407171A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integral forming method for sewing enhanced cross connector made of fiber reinforced resin matrix composite |
| CN103407171B (en) * | 2013-07-30 | 2015-07-15 | 北京航空航天大学 | Integral forming method for sewing enhanced cross connector made of fiber reinforced resin matrix composite |
| CN103639101A (en) * | 2013-11-15 | 2014-03-19 | 西安航空动力股份有限公司 | Method for coating abradable coating of composite containing ring of aircraft engine |
| CN104386129A (en) * | 2014-10-22 | 2015-03-04 | 徐东 | Automobile radiator crossbeam made of fiber reinforced composite material and manufacturing method thereof |
| CN106671443B (en) * | 2015-11-05 | 2020-10-27 | 空中巴士运营有限公司 | Method for manufacturing an apertured frame for an aircraft fuselage, forming and injection moulding tool and apertured frame obtained thereby |
| CN106671443A (en) * | 2015-11-05 | 2017-05-17 | 空中巴士运营有限公司 | Method, forming and injection tool for manufacturing aperture surrounding frame for aircraft fuselage, and the frame obtained thereof |
| CN107139507B (en) * | 2017-06-15 | 2019-04-16 | 西安交通大学 | A kind of high crash-worthiness cylindrical structure forming method of composite material |
| CN107139507A (en) * | 2017-06-15 | 2017-09-08 | 西安交通大学 | A kind of high crash-worthiness cylindrical structure forming method of composite |
| CN111051585B (en) * | 2017-08-30 | 2022-01-28 | 赛峰飞机发动机公司 | Woven fiber structure for forming shell preform |
| CN111051585A (en) * | 2017-08-30 | 2020-04-21 | 赛峰飞机发动机公司 | Woven fiber structure for forming shell preform |
| CN111267373A (en) * | 2018-12-05 | 2020-06-12 | 湖南易净环保科技有限公司 | Method for producing damp-proof insulating pipe for live working by squeezing, drawing and winding |
| CN110849738A (en) * | 2019-12-09 | 2020-02-28 | 湖南崇德工业科技有限公司 | Fiber reinforced composite material winding mandrel, winding tool and stretching tool |
| CN111912619A (en) * | 2020-06-01 | 2020-11-10 | 浙江海骆航空科技有限公司 | Axial containment test device and method for turbine engine exhaust casing |
| CN113858650A (en) * | 2020-06-30 | 2021-12-31 | 中国航发商用航空发动机有限责任公司 | Method for manufacturing composite annular parts |
| CN112412878A (en) * | 2020-09-30 | 2021-02-26 | 航天材料及工艺研究所 | Capturing type ballistic impact resistant composite material fan casing and manufacturing method thereof |
| CN112412878B (en) * | 2020-09-30 | 2022-04-12 | 航天材料及工艺研究所 | Capturing type ballistic impact resistant composite material fan casing and manufacturing method thereof |
| CN114643725A (en) * | 2020-12-21 | 2022-06-21 | 中国航发商用航空发动机有限责任公司 | Manufacturing method of composite casing and composite casing |
| CN114643725B (en) * | 2020-12-21 | 2024-04-26 | 中国航发商用航空发动机有限责任公司 | Manufacturing method of composite casing and composite casing |
| CN112848378A (en) * | 2020-12-26 | 2021-05-28 | 吉林大学 | Fiber reinforced composite blade material with bionic structure and preparation method thereof |
| CN113290966A (en) * | 2021-05-21 | 2021-08-24 | 山东中恒景新碳纤维科技发展有限公司 | Multilayer woven fiber composite material and application thereof, ski vehicle shell and preparation method thereof |
| CN113524719A (en) * | 2021-06-28 | 2021-10-22 | 武汉理工大学 | Curing self-tightening heat treatment integrated process for metal lining fiber winding gas storage cylinder |
| CN113524719B (en) * | 2021-06-28 | 2024-04-30 | 武汉理工大学 | Curing self-tightening heat treatment integrated process for metal lining fiber winding gas cylinder |
| CN116001307A (en) * | 2021-10-22 | 2023-04-25 | 中国科学院宁波材料技术与工程研究所 | Composite plate spring and preparation method thereof |
| CN115352102A (en) * | 2022-07-29 | 2022-11-18 | 中国航发沈阳发动机研究所 | Manufacturing method of composite material containing ring for engine case and engine case |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101723086A (en) | Containing ring of aircraft engine fan made of fiber-reinforced composite material | |
| US8074826B2 (en) | Damage and leakage barrier in all-composite pressure vessels and storage tanks | |
| US8475895B2 (en) | Articles comprising composite structures having mounting flanges | |
| US10190240B2 (en) | Woven preform, composite, and method of making thereof | |
| US8966754B2 (en) | Methods for reducing stress on composite structures | |
| JP4639085B2 (en) | Pressure vessel and method for manufacturing the same | |
| EP1927731B1 (en) | Methods for making structures having mounting flanges | |
| EP2729296B1 (en) | Wind turbine blade comprising metal filaments and carbon fibres and a method of manufacturing thereof | |
| US20050211082A1 (en) | Fabrics, tows of continuous filaments and strands for forming layers of reinforcement for a composite element with a resin matrix | |
| US11078839B2 (en) | Composite nosecone | |
| CN102211405A (en) | Process for forming light-weight and high-pressure gas bottle made of composite material | |
| CN104743087B (en) | A kind of ship D braided composites propeller blade and preparation method thereof | |
| WO2014065281A1 (en) | Cylindrical case and process for producing cylindrical case | |
| US20120251305A1 (en) | Impactor containment | |
| JP5020031B2 (en) | Method of making a composite structure having a mounting flange | |
| CN210372853U (en) | Three-dimensional woven pressure gas cylinder | |
| CN109941408B (en) | Carbon fiber composite material deep diving pressure-resistant cabin and preparation method thereof | |
| US20080115339A1 (en) | Apparatus for use with structures having mounting flanges | |
| US11346499B1 (en) | Containers and methods for protecting pressure vessels | |
| CN210126324U (en) | Novel high-strength fiber pultrusion pipeline | |
| CN203273275U (en) | Steel wire winding structure high-pressure gas cylinder | |
| CN108139024B (en) | Pressure vessel with continuous fibers | |
| CN112709612B (en) | Enclosed casing, aircraft engine and manufacturing method of enclosed casing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20100609 |