CN109210003A - Fan contains casing and preparation method thereof - Google Patents
Fan contains casing and preparation method thereof Download PDFInfo
- Publication number
- CN109210003A CN109210003A CN201710527600.7A CN201710527600A CN109210003A CN 109210003 A CN109210003 A CN 109210003A CN 201710527600 A CN201710527600 A CN 201710527600A CN 109210003 A CN109210003 A CN 109210003A
- Authority
- CN
- China
- Prior art keywords
- main frame
- casing
- fan
- area
- enhancement layer
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
- B29C70/086—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of pure plastics material, e.g. foam layers
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2305/00—Use of metals, their alloys or their compounds, as reinforcement
- B29K2305/08—Transition metals
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention provides a kind of fans to contain casing, it is enclosed in around the fan of aero-engine, it includes main frame that the fan, which contains casing, the main frame includes the side wall of tubular and the flange positioned at side wall both ends, the main frame is made of carbon fiber resin matrix composite, the side wall of the main frame axially includes containing area and the non-inclusive area positioned at the containing area both sides along casing, it is equipped with the inclusive layer circumferentially distributed along casing in the containing area of the inside sidewalls of the main frame, which is made of the polymer matrix composites of carbon fiber and aramid fiber shuffling.
Description
Technical field
The present invention relates to aero-engine composite material fancase design fields, more particularly to one kind to have mixed structure
Contain casing and preparation method thereof with the fan of composite material.
Background technique
Fan contains the important component that casing is aero-engine, and effect is that accident occurs in fan blade to fall off or damage
Bad when, can contain the fan blade to fall off or fragment, prevent its further destruction to engine and aircaft configuration.
While the design requirement that fan contains casing guarantees enough rigidity, there is very excellent containing ability, this is just
The design for containing casing to fan proposes very high requirement.Aero-engine generallys use following several modes and realizes fan
The inclusive design of casing:
1. traditional aero-engine mostly uses greatly all-metal material (high-strength steel, titanium alloy, aluminium alloy) to manufacture, in order to protect
The overall stiffness of card thin-wall construction casing is met the requirements, and designs ring stiffener, on the outside of Thin-Wall Outer Casing mostly to promote its entirety
Rigidity, while casing weight can also be reduced.
2. second of case structure mostly uses the containing casing of aramid fiber winding arrangement, the design concept of the casing be
Meet reduces casing weight on the basis of inclusiveness as far as possible, therefore uses the light materials such as Kevlar, the structure of this casing
Metal material is milled into thin-wall construction as casing main frame, but by aluminium alloy or titanium alloy, in order to promote its inclusiveness,
Aluminum honeycomb and aramid fabric are wrapped up outside aluminium alloy or titanium alloy casing again, in order to meet its inclusiveness, which is usually wrapped up
Tens of layers, even tens layers, this casing is compared with pure metal casing, lighter in weight, but relatively cumbersome, and aramid fiber is fine in addition
Tie up moisture-sensitive, not corrosion-resistant, aramid fabric protected although using resin, to resin surface progress waterproof at
Reason causes it to hold corrosion-vulnerable, maintainable also poor.
3. the third casing uses fibre reinforced composite material, the casing of the structure uses the carbon of two-dimentional three-dimensional
Then fibrage is wound to required thickness at cloth around engine shaft, then inject epoxy resin using RTM technique, such
The maximum feature of casing be it is light-weight, in order to improve the stress distribution after it is hit and crack propagation, foreign countries also have at such
The design of the outside package metal mesh of casing, to realize whole enhancing and Anticrack.On the other hand, excellent for realization structure
To change, such casing can be designed to the feature that there is non-uniform thickness to be distributed, and containment region thickness is greater than non-inclusive region, but
Since such casing is using winding process, cause the feature of its non-uniform thickness relatively difficult to achieve.More importantly such
Casing can only be using the containing realized to composite material fan blade.
It is, therefore, desirable to provide a kind of novel mixed structure/material fan contains casing, contain meeting aero-engine
Property under the premise of, using light material, technical ability realize loss of weight may be implemented again to composite material fan blade and metal fan leaf
The containing of piece.
Summary of the invention
A brief summary of one or more aspects is given below to provide to the basic comprehension in terms of these.This general introduction is not
The extensive overview of all aspects contemplated, and be both not intended to identify critical or decisive element in all aspects also non-
Attempt to define the range in terms of any or all.Its unique purpose is to provide the one of one or more aspects in simplified form
A little concepts are with the sequence for more detailed description given later.
According to an aspect of the present invention, a kind of fan containing casing is provided, is enclosed in around the fan of aero-engine,
It includes main frame that the fan, which contains casing, which includes the side wall of tubular and the flange positioned at side wall both ends, the master
Frame is made of carbon fiber resin matrix composite, and the side wall of the main frame axially includes containing area and positioned at the containing along casing
The non-inclusive area of area both sides is equipped with the inclusive layer circumferentially distributed along casing in the containing area of the inside sidewalls of the main frame, should
Inclusive layer is made of the polymer matrix composites of carbon fiber and aramid fiber shuffling.
In one example, which includes the multiple reinforcement blocks circumferentially distributed along casing.
In one example, the containing area sidewall thickness of the main frame is greater than non-inclusive area's sidewall thickness.
In one example, the side wall minimum thickness of the main frame is not less than 20mm, contains area's sidewall thickness between 25-35mm
Between.
In one example, the side wall of the main frame and the flange using automatic fiber placement or automated tape-laying technique once at
Type forms.
In one example, the volume content of the carbon fiber of the shuffling inclusive layer and aramid fiber ratio is 2:1.
In one example, more reinforced supports are circumferentially uniformly distributed along casing in the side-wall outer side of the main frame, every adds
On the flange for the front and rear edge that strong bracket is axially fixed at the main frame along casing.
In one example, which is titanium alloy pipe, and every reinforced support is fixed by bolted connection
In on the flange of the front and rear edge of the main frame.
In one example, there are gaps between the reinforced support and the side wall of the main frame.
In one example, the gap is between 8-12mm.
It further includes tearing open to be wound on the more reinforced supports that be formed by cladding this is more that the fan, which contains casing, in one example
The enhancement layer of root reinforced support, the enhancement layer are made of the polymer matrix composites of carbon fiber and aramid fiber shuffling.
In one example, the containing area enhancement layer thickness of the enhancement layer is greater than non-inclusive area's enhancement layer thickness.
In one example, the containing area enhancement layer thickness of the enhancement layer is not less than 30mm, and non-inclusive area's enhancement layer thickness is situated between
Between 10-15mm.
In one example, a protective layer is wrapped up in the outside of the enhancement layer.
In one example, which includes polyurethane polymer material layer and coated in the polyurethane polymer material
Hydrophobic coat on layer.
According to another aspect of the present invention, a method of being used to prepare fan and contain casing, which contains casing packet
It is trapped among around the fan of aero-engine, this method comprises:
It is coated with using carbon fiber resin matrix composite by craft or the technique completion of automated tape-laying or automatic fiber placement is spread
The molding of the main frame of layer structure, which includes the side wall of tubular and the flange positioned at side wall both ends, the flange
Using whole flanging process one-pass molding, the side wall of the main frame axially includes containing area and positioned at the containing area both sides along casing
Non-inclusive area；
Carbon fiber and aramid fiber are subjected to hybrid three-dimensional braiding simultaneously and resin compounded is to obtain inclusive layer；And
The containing area that the containing is placed on the inside sidewalls of the main frame is made this in a manner of through secondary co-curing
Inclusive layer is connected with the main frame.
In one example, the containing area sidewall thickness of the main frame is greater than non-inclusive area's sidewall thickness.
In one example, the side wall minimum thickness of the main frame is not less than 20mm, contains area's sidewall thickness between 25-35mm
Between.
In one example, the volume content ratio of the carbon fiber and aramid fiber that weave the inclusive layer is 2:1.
In one example, it further includes the side-wall outer side in the main frame along the circumferential equably general of casing which, which contains casing,
On the flange for the front and rear edge that more reinforced supports are fixed on the main frame.
In one example, which is titanium alloy pipe, and every reinforced support is fixed by bolted connection
In on the flange of the front and rear edge of the main frame.
In one example, there are gaps between the reinforced support and the side wall of the main frame.
In one example, the gap is between 8-12mm.
In one example, this method further includes by the shuffling satin fabric of carbon fiber and aramid fiber in certain tensioning
At a slow speed, be uniformly wrapped on the reinforced support under control, and and resin compounded to form enhancement layer.
In one example, the containing area enhancement layer thickness of the enhancement layer is greater than non-inclusive area's enhancement layer thickness.
In one example, the containing area enhancement layer thickness of the enhancement layer is not less than 30mm, and non-inclusive area's enhancement layer thickness is situated between
Between 10-15mm.
In one example, after the completion of winding, interface area uses the epoxy resin with high shear strength to carry out bonding envelope
Dress.
In one example, this method further includes wrapping up a protective layer in the outside of the enhancement layer.
It in one example, should include poly- in the winding of the outside of the enhancement layer in the outside of an enhancement layer package protective layer
Urethane film layer；And hydrophobic coat is sprayed on the polyurethane film.
In one example, after the completion of winding, interface area uses the epoxy resin with high shear strength to carry out bonding envelope
Dress.
Detailed description of the invention
After the detailed description for reading embodiment of the disclosure in conjunction with the following drawings, it better understood when of the invention
Features described above and advantage.In the accompanying drawings, each component is not necessarily drawn to scale, and has similar correlation properties or feature
Component may have same or similar appended drawing reference.
The fan that Fig. 1 shows mixed structure/material aero-engine according to an aspect of the present invention contains machine
The schematic diagram of casket；
Fig. 2 shows the fans of mixed structure/material aero-engine according to an aspect of the present invention to contain machine
The diagrammatic cross-section of casket；
The fan that Fig. 3 shows mixed structure/material aero-engine according to an aspect of the present invention contains machine
The reinforcement block schematic diagram along the distribution of casing frame of casket；
The fan that Fig. 4 shows mixed structure/material aero-engine according to an aspect of the present invention contains machine
The example cross-section schematic diagram of casket；And
The fan that Fig. 5 shows mixed structure/material aero-engine according to an aspect of the present invention contains machine
The schematic diagram of the installation reinforced support of casket.
Specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.Note that below in conjunction with attached drawing and specifically real
The aspects for applying example description is merely exemplary, and is understood not to carry out any restrictions to protection scope of the present invention.
Enough rigidity should be guaranteed by containing casing for fan, guarantee enough inclusiveness again, while reducing as far as possible
The requirement of own wt, the present invention propose that a kind of aerial engine fan of mixed structure/material contains casing 100.Fig. 1 is shown
The fan of mixed structure/material aero-engine according to an aspect of the present invention contains the schematic diagram of casing 100.
It is enclosed in around the fan of aero-engine as shown in Figure 1, fan contains casing 100, is integrally cylindrical in shape.In Fig. 1
Fan contain casing 100 and be truncated a part with the diagrammatic cross-section of schematic diagram 2.
Fig. 2 shows the fans of mixed structure/material aero-engine according to an aspect of the present invention to contain machine
The schematic diagram of the section by casing axis of casket 100.
As shown in Fig. 2, it may include main frame 10 that fan, which contains casing 100,.The side wall 11 of main frame 10 including tubular and
Two flanges 12 positioned at side wall both ends.Two kinds of regions can be axially divided into along casing in the side wall of main frame 10, be packet respectively
Hold area A and positioned at the non-inclusive area B and C for containing the both sides area A.
In the example shown in figure 2, containing area A, be equipped in the inside sidewalls of main frame 10 circumferentially distributed along casing
Inclusive layer 20, to strengthen containing effect.Due to only containing area A equipped with inclusive layer 20, then the premise for containing effect is being enhanced
Under, mitigate fancase weight as much as possible.
Certainly, in other examples, inclusive layer 20 can also be arranged in non-inclusive area.
In the present invention, main frame 10 can be made of carbon fiber resin matrix composite, and inclusive layer 20 can be by carbon fiber
It is made with the polymer matrix composites of aramid fiber shuffling.
Material is answered as main frame using the carbon fiber of thinner thickness and uniform thickness, has biggish loss of weight excellent compared to metal material
Gesture.Inclusive layer of the configuration by carbon fiber and aramid fiber using 3 dimension weaving shufflings, the inclusive layer in the inside of main frame 10
It is evenly arranged on the inside of main frame 10, takes full advantage of that carbon fibre material intensity is high, modulus is high, the characteristics of aramid fiber material good toughness,
Main function is subject to shock loading, realizes and contains.
The characteristics of compared to full composite material casing wall thickness non-uniform Distribution, inclusive layer design, which improves its technique, to be realized
Property with it is maintainable.
In specific practice, fan is prepared using high-strength middle modulus (such as T800) carbon fiber enhancement resin base composite material
The main frame 10 of casing, the side wall 11 of the casing main frame 10 are the main part that fan contains casing 100.To guarantee casing master
The rigidity of frame, 11 minimum thickness of side wall are not less than 20mm, and containment region thickness control is between 25-35mm.
Bolt hole, the side wall 11 and flange of fancase main frame 10 are evenly equipped on flange 12 on casing main frame 10
Side 12 uses automatic fiber placement or automated tape-laying technique one-pass molding.
In one example, inclusive layer 20 includes the multiple reinforcement blocks 21 circumferentially distributed along casing.As an example, in casing master
The inside sidewalls of frame 10 are circumferentially uniformly distributed 6 reinforcement blocks 21 (as shown in Figure 3) along casing, and the reinforcement block 21 is by aramid fiber fibre
Dimension and the composite fibre of T800 fiber shuffling enhance composite material.The effect of the reinforcement block 21 is to influence maximum θ to being hit
Angular zone carries out local strengthening.
The reinforcement block 21 uses 3 dimension mixed weaving structures of aramid fiber and carbon fiber fiber, aramid fiber and carbon fiber
The volume content ratio of dimension is 2:1.The existing very high intensity of the reinforcement block and modulus are ensured that in this way, and are had extraordinary tough
Property, when the foreign object impact region, it can effectively promote the anti-foreign object impact lesion capability of casing.
In one example, more reinforced supports 30 are circumferentially uniformly distributed along casing in the side-wall outer side of main frame 10, every
Reinforced support 30 is axially fixed on the flange 12 of the front and rear edge of main frame 10 along casing.Fig. 5 shows according to the present invention
The fan of mixed structure/material aero-engine of one side contains the schematic diagram of the installation reinforced support of casing 100.
As shown in figure 5, the outer lateral edge casing of side wall 11 in main frame 10 is circumferentially uniformly distributed more reinforced supports 30, every
Reinforced support 30 is axially fixed on the flange 12 of the front and rear edge of main frame 10 along casing.
In one example, 8-12 root titanium alloy metal reinforced support 30 is uniformly distributed in 10 outer layer of fancase main frame.
To mitigate weight, which can be high-strength titanium alloy pipes.
The mode that the titanium alloy metal reinforced support 30 is connected by screw bolts is fixed on the front and back of fancase main frame 10
On edge flange 12.To guarantee its maintainable and installation, the side wall 11 of metal reinforced support 30 and casing main frame 10 it
Between there are the spaces 40 of 8-12mm.
The metal reinforced support 30 can not only improve the overall stiffness of casing main frame 10, can also be in casing main frame
10 by foreign object impact when, effectively absorption impact energy, improve casing main frame 10 stress distribution, while can also for as scheme
The outside offer support (as described below) of enhancement layer 50 shown in 2.
Space 40 between the side wall 11 of metal reinforced support 30 and casing main frame 10 as shown in the figure, can effectively change
Kind fan contains the maintenanceability and assembling capacity of casing 100, when the outside enhancement layer 50 because raindrop erosion damages
When, it may be convenient to it is dispelled and is repaired, while will not be because directly being contacted due to etching machine with casing main frame 10
Casket ontology.
A circle high-strength titanium alloy pipes are configured with as braced frame along casing surrounding again on the outside of main frame, and with ring
The metal material integral casing of shape reinforcing rib is compared, and the casing for being configured with high-strength titanium alloy support frame can both increase entire main frame
The rigidity of frame, and energy can be effectively absorbed when main frame absorbs impact load, reduce casing deformation, meets with and impact in casing
When load, the titanium alloy frame can capture penetrate inclusive layer and main frame fly off object (especially metal flies off object).
As shown in Fig. 2, fan containing casing 100, which may also include to tear open to be wound on reinforced support 30, is formed by cladding this more
The enhancement layer 50 in the outside of reinforced support 30.Enhancement layer 50 can be by the polymer matrix composites system of carbon fiber and aramid fiber shuffling
At.
In one example, carbon fiber/aramid fiber mixing enhancing that 10-30mm thickness can be covered on reinforced support 30 is compound
Material.The thickness distribution of the enhancement layer 50 is discontinuous, such as contains area's enhancement layer thickness and be greater than non-inclusive area enhancing thickness
Degree.
Specifically, the outside enhancement layer 50 of fancase non-inclusive region B, C are with a thickness of 10-15mm；Fancase contains
The outside enhancement layer thickness of region A should be not less than 30mm.But its actual (real) thickness should contain simulation analysis or examination according to fancase
Result is tested to determine.It should be noted that the corresponding angle, θ of containment region A is different for the engine of different model.
The main function of the enhancement layer 50 in outside is to fall off once fan blade occurs, and puncture casing main frame 10
In the case of, the fan blade to fly out or relic are captured, further to guarantee the safety of engine and aircraft.
Finally, can the outside of enhancement layer 50 on the outside wrap up one layer of polyurethane polymer material, then in the polyurethane polyureas
It closes object outer material side and coats hydrophobic coat, above structure is referred to as protective layer 60.The effect of hydrophobic coat is in the protective layer 60
Reduce contact of the rainwater with casing to the greatest extent, the effect of polyurethane material is the contact for preventing casing with rainwater, to prevent from taking for a long time
In the case where labour, erosion of the rainwater to composite material.
The fan that Fig. 4 shows mixed structure/material aero-engine according to an aspect of the present invention contains machine
The example cross-section schematic diagram of casket.
By being reconfigured carbon fiber and aramid fiber reinforced composite enhancement layer on the outside of main frame, main auxiliary, which contains, to be made
With, therefore compared with aramid fiber winds enhancing casing, the enhancement layer thickness is small, and does not need configuration honeycomb.To mitigate
Corrosion of the rainwater to composite material finally configures a protective layer on the outside of casing, and coats hydrophobic coat, reduces rainwater to the greatest extent
Contact with casing.
Fan, which contains casing 100, can be respectively adopted carbon fiber resin matrix composite, three kinds of titanium alloy, high tenacity aramid fiber etc.
Material plays the characteristic of above-mentioned three kinds of materials by specific structure type respectively, realizes casing rigidity, containment properties and loss of weight
The coordinating and unifying, realize and contain metal and multiple material blade, and is light-weight.
The example that fan introduced below contains the preparation method of casing.
Step 1: elder generation is coated with according to design drawing using craft or the technique of automated tape-laying or automatic fiber placement, completes laying knot
The molding of structure carbon fibre composite casing main frame.
The side wall and flange of the casing main frame are using whole flanging process, one-pass molding.
Step 2: according to casing size, using 3 dimension shuffling techniques, by aramid fiber and carbon fiber according to volume content 2:1
Inside inclusive layer is prepared after carrying out hybrid three-dimensional braiding, with high tenacity resin compounded.
Step 3: the mode that secondary co-curing can be used with casing main frame in inside inclusive layer connects into an entirety.
Step 4: the mode that can be connected by screw bolts more (for example, 12) titanium alloy pipes is clamped with the main frame of casing
Frame forms titanium alloy metal reinforced support.
The casing for installing reinforced support is as shown in Figure 5.
Step 6: can by carbon fiber/aramid fiber shuffling satin fabric under the control of certain tensioning at a slow speed, uniformly
Be wrapped on titanium alloy metal reinforced support, and and resin compounded with formed outside enhancement layer.
After the completion of to be wound, interface area uses the epoxy resin with high shear strength to carry out bonding encapsulation.
Step 7: using the polyurethane film of certain thickness (such as 0.2-0.4mm), be wound outside enhancement layer on the outside.
After the completion of to be wound, bonding encapsulation is equally carried out using the epoxy resin with high shear strength in interface area.
The hydrophobic coat that a layer thickness is no more than 0.5-0.8mm is finally sprayed on the outside of polyurethane film.
Although for simplify explain the above method is illustrated to and is described as a series of actions, it should be understood that and understand,
The order that these methods are not acted is limited, because according to one or more embodiments, some movements can occur in different order
And/or with from it is depicted and described herein or herein it is not shown and describe but it will be appreciated by those skilled in the art that other
Movement concomitantly occurs.
Offer is to make any person skilled in the art all and can make or use this public affairs to the previous description of the disclosure
It opens.The various modifications of the disclosure all will be apparent for a person skilled in the art, and as defined herein general
Suitable principle can be applied to other variants without departing from the spirit or scope of the disclosure.The disclosure is not intended to be limited as a result,
Due to example described herein and design, but should be awarded and principle disclosed herein and novel features phase one
The widest scope of cause.
Claims (30)
1. a kind of fan contains casing, it is enclosed in around the fan of aero-engine, it includes main frame that the fan, which contains casing,
The main frame includes that the side wall of tubular and the flange positioned at side wall both ends, the main frame are compound by carbon fibre resin base
Material is made, the side wall of the main frame along casing axially include contain area and positioned at it is described contain area both sides non-inclusive area,
It is equipped with the inclusive layer circumferentially distributed along casing in the containing area of the inside sidewalls of the main frame, the inclusive layer is by carbon fiber
It ties up and is made with the polymer matrix composites of aramid fiber shuffling.
2. fan as described in claim 1 contains casing, which is characterized in that the inclusive layer includes circumferentially distributed along casing
Multiple reinforcement blocks.
3. fan as described in claim 1 contains casing, which is characterized in that the containing area sidewall thickness of the main frame is greater than
Non-inclusive area's sidewall thickness.
4. fan as claimed in claim 3 contains casing, which is characterized in that the side wall minimum thickness of the main frame is not less than
20mm contains area's sidewall thickness between 25-35mm.
5. fan as described in claim 1 contains casing, which is characterized in that the side wall and the flange of the main frame
Side is formed using automatic fiber placement or automated tape-laying technique one-pass molding.
6. fan as described in claim 1 contains casing, which is characterized in that the carbon fiber and aramid fiber of inclusive layer described in shuffling are fine
The volume content ratio of dimension is 2:1.
7. fan as described in claim 1 contains casing, which is characterized in that all along casing in the side-wall outer side of the main frame
To more reinforced supports are uniformly distributed, every reinforced support is axially fixed at the flange of the front and rear edge of the main frame along casing
On.
8. fan as claimed in claim 7 contains casing, which is characterized in that the reinforced support is titanium alloy pipe, every
Reinforced support is fixed on by bolted connection on the flange of the front and rear edge of the main frame.
9. fan as claimed in claim 7 contains casing, which is characterized in that the side wall of the reinforced support and the main frame
Between there are gaps.
10. fan as claimed in claim 9 contains casing, which is characterized in that the gap is between 8-12mm.
11. fan as claimed in claim 7 contains casing, which is characterized in that further include tearing open to be wound on the more reinforced supports
On be formed by the enhancement layer for coating the more reinforced supports, the enhancement layer by carbon fiber and aramid fiber shuffling resin
Based composites are made.
12. fan as claimed in claim 11 contains casing, which is characterized in that the containing area enhancement layer thickness of the enhancement layer
Greater than non-inclusive area's enhancement layer thickness.
13. fan as claimed in claim 12 contains casing, which is characterized in that the containing area enhancement layer thickness of the enhancement layer
Not less than 30mm, non-inclusive area's enhancement layer thickness is between 10-15mm.
14. fan as claimed in claim 11 contains casing, which is characterized in that wrap up one layer of guarantor in the outside of the enhancement layer
Sheath.
15. fan as claimed in claim 14 contains casing, which is characterized in that the protective layer includes polyether polyols material
The bed of material and coated in the hydrophobic coat on the polyurethane polymer material layer.
16. a kind of method for being used to prepare fan and containing casing, the fan contain the fan that casing is enclosed in aero-engine
Around, which comprises
Using carbon fiber resin matrix composite by being coated with by hand or the technique of automated tape-laying or automatic fiber placement completes laying knot
The molding of the main frame of structure, the main frame include the side wall of tubular and the flange positioned at side wall both ends, the flange
Using whole flanging process one-pass molding, the side wall of the main frame axially includes containing area and positioned at the containing area along casing
The non-inclusive area of both sides；
Carbon fiber and aramid fiber are subjected to hybrid three-dimensional braiding simultaneously and resin compounded is to obtain inclusive layer；And
The containing area of the inside sidewalls for containing and being placed on the main frame is made in a manner of through secondary co-curing
The inclusive layer is connected with the main frame.
17. the method described in claim 16, which is characterized in that the containing area sidewall thickness of the main frame is greater than non-inclusive
Area's sidewall thickness.
18. method as claimed in claim 17, which is characterized in that the side wall minimum thickness of the main frame is not less than 20mm,
Contain area's sidewall thickness between 25-35mm.
19. the method described in claim 16, which is characterized in that weave the carbon fiber of the inclusive layer and the body of aramid fiber
Product content ratio is 2:1.
20. the method described in claim 16, which is characterized in that further include:
The main frame side-wall outer side along casing circumferentially more reinforced supports are equably fixed on the main frame before
On the flange of rear.
21. method as claimed in claim 20, which is characterized in that the reinforced support is titanium alloy pipe, every reinforcement branch
Frame is fixed on by bolted connection on the flange of the front and rear edge of the main frame.
22. method as claimed in claim 20, which is characterized in that stayed between the reinforced support and the side wall of the main frame
There is gap.
23. method as claimed in claim 22, which is characterized in that the gap is between 8-12mm.
24. method as claimed in claim 20, which is characterized in that further include:
The shuffling satin fabric of carbon fiber and aramid fiber at a slow speed, is uniformly wrapped under the control of certain tensioning described
On reinforced support, and and resin compounded to form enhancement layer.
25. method as claimed in claim 24, which is characterized in that the containing area enhancement layer thickness of the enhancement layer is greater than non-packet
Hold area's enhancement layer thickness.
26. method as claimed in claim 25, which is characterized in that the containing area enhancement layer thickness of the enhancement layer is not less than
30mm, non-inclusive area's enhancement layer thickness is between 10-15mm.
27. method as claimed in claim 24, which is characterized in that after the completion of winding, interface area, which uses, has high shear strong
The epoxy resin of degree carries out bonding encapsulation.
28. method as claimed in claim 24, which is characterized in that further include:
A protective layer is wrapped up in the outside of the enhancement layer.
29. method as claimed in claim 28, which is characterized in that wrap up a protective layer in the outside in the enhancement layer
Include:
Polyurethane film is wound in the outside of the enhancement layer；And
Hydrophobic coat is sprayed on the polyurethane film.
30. method as claimed in claim 29, which is characterized in that after the completion of winding, interface area, which uses, has high shear strong
The epoxy resin of degree carries out bonding encapsulation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710527600.7A CN109210003B (en) | 2017-06-30 | 2017-06-30 | Fan containing casing and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710527600.7A CN109210003B (en) | 2017-06-30 | 2017-06-30 | Fan containing casing and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109210003A true CN109210003A (en) | 2019-01-15 |
| CN109210003B CN109210003B (en) | 2022-02-08 |
Family
ID=64992071
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710527600.7A Active CN109210003B (en) | 2017-06-30 | 2017-06-30 | Fan containing casing and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109210003B (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110307182A (en) * | 2019-07-03 | 2019-10-08 | 洛阳北玻台信风机技术有限责任公司 | A kind of carbon fiber and expanding material combined type ducted fan air duct and its forming method |
| CN111852948A (en) * | 2019-04-24 | 2020-10-30 | 中国航发商用航空发动机有限责任公司 | Turbofan engine, fan case and manufacturing method thereof |
| CN112081636A (en) * | 2019-06-12 | 2020-12-15 | 中国航发商用航空发动机有限责任公司 | Inclusive fan casing |
| 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 |
| CN112280328A (en) * | 2019-07-24 | 2021-01-29 | 中国航发商用航空发动机有限责任公司 | Engine fan containing casing and preparation method thereof |
| CN112538679A (en) * | 2020-11-02 | 2021-03-23 | 南京玻璃纤维研究设计院有限公司 | Hollow box-shaped reinforcement body, preparation method thereof and preparation method of hollow box |
| CN112696241A (en) * | 2020-12-23 | 2021-04-23 | 南京航空航天大学 | Three-dimensional braided composite material casing with variable braiding angle and design method |
| CN112696240A (en) * | 2020-12-23 | 2021-04-23 | 南京航空航天大学 | Distributed containing casing and containing method |
| CN112877862A (en) * | 2021-01-04 | 2021-06-01 | 南京玻璃纤维研究设计院有限公司 | Preparation method of revolving body preform and preparation method of revolving body |
| CN114055805A (en) * | 2020-08-10 | 2022-02-18 | 中国航发商用航空发动机有限责任公司 | Manufacturing method of easily-worn ring of aircraft engine fan |
| CN114060305A (en) * | 2020-07-29 | 2022-02-18 | 中国航发商用航空发动机有限责任公司 | Fan containing casing and preparation method thereof |
| CN114151384A (en) * | 2020-09-07 | 2022-03-08 | 中国航发商用航空发动机有限责任公司 | Turbofan engine and casing thereof |
| CN114542516A (en) * | 2020-11-26 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Composite material 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2426287B (en) * | 2005-05-18 | 2007-05-30 | Rolls Royce Plc | Blade containment structure |
| WO2008156890A2 (en) * | 2007-04-02 | 2008-12-24 | A & P Technology, Inc. | Composite case armor for jet engine fan case containment |
| US20160281738A1 (en) * | 2012-07-02 | 2016-09-29 | United Technologies Corporation | Functionally graded composite fan containment case |
| CN106794639A (en) * | 2014-08-22 | 2017-05-31 | 赛峰飞机发动机公司 | The self-reinforcing housing being made up of the composite with organic matrix |
| WO2017109403A1 (en) * | 2015-12-22 | 2017-06-29 | Safran Aircraft Engines | Lighter-weight casing made of composite material and method of manufacturing same |
-
2017
- 2017-06-30 CN CN201710527600.7A patent/CN109210003B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2426287B (en) * | 2005-05-18 | 2007-05-30 | Rolls Royce Plc | Blade containment structure |
| WO2008156890A2 (en) * | 2007-04-02 | 2008-12-24 | A & P Technology, Inc. | Composite case armor for jet engine fan case containment |
| US20160281738A1 (en) * | 2012-07-02 | 2016-09-29 | United Technologies Corporation | Functionally graded composite fan containment case |
| CN106794639A (en) * | 2014-08-22 | 2017-05-31 | 赛峰飞机发动机公司 | The self-reinforcing housing being made up of the composite with organic matrix |
| WO2017109403A1 (en) * | 2015-12-22 | 2017-06-29 | Safran Aircraft Engines | Lighter-weight casing made of composite material and method of manufacturing same |
Non-Patent Citations (1)
| Title |
|---|
| 沈观林: "《复合材料力学》", 28 February 1996, 清华大学出版社 * |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111852948A (en) * | 2019-04-24 | 2020-10-30 | 中国航发商用航空发动机有限责任公司 | Turbofan engine, fan case and manufacturing method thereof |
| CN111852948B (en) * | 2019-04-24 | 2022-01-28 | 中国航发商用航空发动机有限责任公司 | Turbofan engine, fan case and manufacturing method thereof |
| CN112081636B (en) * | 2019-06-12 | 2022-04-19 | 中国航发商用航空发动机有限责任公司 | Inclusive fan casing |
| CN112081636A (en) * | 2019-06-12 | 2020-12-15 | 中国航发商用航空发动机有限责任公司 | Inclusive fan casing |
| CN110307182B (en) * | 2019-07-03 | 2024-06-07 | 洛阳北玻三元流风机技术有限公司 | Carbon fiber and expansion material combined duct fan dryer and forming method thereof |
| CN110307182A (en) * | 2019-07-03 | 2019-10-08 | 洛阳北玻台信风机技术有限责任公司 | A kind of carbon fiber and expanding material combined type ducted fan air duct and its forming method |
| CN112280328A (en) * | 2019-07-24 | 2021-01-29 | 中国航发商用航空发动机有限责任公司 | Engine fan containing casing and preparation method thereof |
| CN114060305A (en) * | 2020-07-29 | 2022-02-18 | 中国航发商用航空发动机有限责任公司 | Fan containing casing and preparation method thereof |
| CN114055805B (en) * | 2020-08-10 | 2023-09-08 | 中国航发商用航空发动机有限责任公司 | Manufacturing method of easy-to-wear ring of aero-engine fan |
| CN114055805A (en) * | 2020-08-10 | 2022-02-18 | 中国航发商用航空发动机有限责任公司 | Manufacturing method of easily-worn ring of aircraft engine fan |
| CN114151384A (en) * | 2020-09-07 | 2022-03-08 | 中国航发商用航空发动机有限责任公司 | Turbofan engine and casing thereof |
| CN112182800B (en) * | 2020-09-18 | 2022-12-20 | 中国航发四川燃气涡轮研究院 | Cylindrical case laying layer design method of resin-based composite material |
| 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 |
| CN112538679A (en) * | 2020-11-02 | 2021-03-23 | 南京玻璃纤维研究设计院有限公司 | Hollow box-shaped reinforcement body, preparation method thereof and preparation method of hollow box |
| CN112538679B (en) * | 2020-11-02 | 2022-07-12 | 南京玻璃纤维研究设计院有限公司 | Hollow box-shaped reinforcement body, preparation method thereof and preparation method of hollow box |
| CN114542516A (en) * | 2020-11-26 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Composite material 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 |
| CN112696240A (en) * | 2020-12-23 | 2021-04-23 | 南京航空航天大学 | Distributed containing casing and containing method |
| CN112696241A (en) * | 2020-12-23 | 2021-04-23 | 南京航空航天大学 | Three-dimensional braided composite material casing with variable braiding angle and design method |
| CN112877862B (en) * | 2021-01-04 | 2022-04-15 | 南京玻璃纤维研究设计院有限公司 | Preparation method of revolving body preform and preparation method of revolving body |
| CN112877862A (en) * | 2021-01-04 | 2021-06-01 | 南京玻璃纤维研究设计院有限公司 | Preparation method of revolving body preform and preparation method of revolving body |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109210003B (en) | 2022-02-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109210003A (en) | Fan contains casing and preparation method thereof | |
| US10724397B2 (en) | Case with ballistic liner | |
| RU2608983C2 (en) | Aircraft with fuselage engines and inner screen | |
| US6814541B2 (en) | Jet aircraft fan case containment design | |
| CA2674061C (en) | Fan case for turbofan engine | |
| US5392514A (en) | Method of manufacturing a composite blade with a reinforced leading edge | |
| JP3636722B2 (en) | Aircraft fan container structure fixing method | |
| CA2664051C (en) | Composite fan case with integral containment zone | |
| US5222297A (en) | Composite blade manufacture | |
| US20060093847A1 (en) | Composite sandwich with improved ballistic toughness | |
| CA2889366C (en) | Cylindrical case and manufacturing method of cyclindrical case | |
| US10443617B2 (en) | Functionally graded composite fan containment case | |
| US9670788B2 (en) | Composite aerofoil vane | |
| US20180127081A1 (en) | Panel structure for an aircraft and manufacturing method thereof | |
| JP4620664B2 (en) | Radome with polyester-polyarylate fibers and method for producing the same | |
| CN106143789B (en) | A kind of submarine pressure hull and preparation method thereof | |
| CN108995265B (en) | Big L/D ratio winds shell cable hood Preembedded method | |
| CN110344887A (en) | Mixing material fan blade and preparation method thereof | |
| CN108481762A (en) | A kind of rocket composite core grade cover board and preparation method thereof | |
| GB2471465A (en) | Fan casing for a turbofan gas turbine engine | |
| US7736719B2 (en) | Protection panel for aircrafts | |
| RU2577975C2 (en) | Leading edge structure, particularly, to aircraft engine nacelle | |
| RU2011117093A (en) | SHELL COMPONENT FOR AIR OR SPACE AIRCRAFT | |
| CN112696240B (en) | Distributed containing casing and containing method | |
| JPH08151000A (en) | Integral fuel tank |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |