CN109555603A - A kind of composite material sealing cover and preparation method thereof - Google Patents
A kind of composite material sealing cover and preparation method thereof Download PDFInfo
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- CN109555603A CN109555603A CN201710890126.4A CN201710890126A CN109555603A CN 109555603 A CN109555603 A CN 109555603A CN 201710890126 A CN201710890126 A CN 201710890126A CN 109555603 A CN109555603 A CN 109555603A
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- composite material
- prepreg
- inside panel
- seal closure
- panel
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Combustion & Propulsion (AREA)
- Composite Materials (AREA)
- General Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Gasket Seals (AREA)
Abstract
The present invention provides a kind of composite material sealing covers, to cooperatively form sealing structure with comb toothing, the seal closure includes inside panel and exterior panel, by drawing stomatal limiting value tap air channel on the inside panel between the inside panel and the exterior panel, the composite material uses bimaleimide resin and glass fabric material.The present invention also provides a kind of methods for being used to prepare above-mentioned composite material sealing cover, specifically include: prepreg is made in bimaleimide resin sized glass fibres cloth by step a；Step b utilizes prepreg described in mold laying；Step c forms the prepreg after laying to obtain the inside panel of the seal closure and the exterior panel and step d, forms the bleed hole on the inside panel.
Description
Technical field
The present invention relates to a kind of composite material sealing covers and preparation method thereof, more particularly to one kind to be used for aviation engine shaft
Hold the oil-resistant high-temperature composite material sealing cover and preparation method thereof of chamber.
Background technique
In order to avoid in bearing bore outside oil and gas leakage to bearing bore in aero-engine mechanical system drive mechanism, in bearing
It is equipped with sealing structure before and after chamber, application is more mature for comb toothing at present, and the component matched with comb tooth sealing structure is
Seal closure, its material of the operating environment requirements of seal closure have high temperature resistant, generally need resistance to 200 DEG C, and need to have oil resistant characteristic simultaneously
Guarantee some strength.
The seal closure of domestic air mail engine bearing chamber selects metal material at present, and traditional metal material seal closure is close
Degree is higher, can not be engine loss of weight, can not achieve the target of aero-engine high efficiency, low oil consumption.External organic type uses
Glass fiber reinforced polyester acid imide is manufactured composite material sealing cover, although glass fiber reinforced polyester acid imide density is low,
And there is good high temperature resistant and oil resistant characteristic, but polyimides is at high cost, indissoluble infusibility, moulding process stability is poor, molding
Technique is difficult to control.And the imido prepreg of glass fiber reinforced polyester is during the preparation process, and solvent is difficult volatilization completely, residual
The solvent stayed can be released in composite molding, cause to generate hole in product, and the intensity and quality of product are all by one
Fixing is rung.
Therefore, a kind of composite material sealing cover is needed, the leakproofness, resistance to of Aero-engine Bearing chamber sealing ring had both been able to satisfy
High temperature, oil resistant and strength characteristics, while the composite material sealing cover of realization can be facilitated using composite material manufacturing technology again.
Summary of the invention
The purpose of the present invention is to provide a kind of composite material sealing covers for Aero-engine Bearing chamber, have low close
Degree, high temperature resistant, oil resistant simultaneously have some strength, constitute sealing structure to cooperate with comb toothing, realize that leakproofness mentions simultaneously
High aeroplane engine engine efficiency reduces oil consumption.The object of the invention is also to provide a kind of preparations of above-mentioned composite material sealing cover
Method.
In order to achieve the above objectives, described provided by the present invention for the composite material sealing cover of Aero-engine Bearing chamber
Seal closure is matched with a comb toothing to form sealing structure, and the seal closure includes inside panel and exterior panel, the inner wall
By drawing stomatal limiting value tap air channel on the inside panel between plate and the exterior panel, the composite material using span come
Imide resin and glass fabric material.
Such as above-mentioned composite material sealing cover, the inside panel is class hubbed flange structure, including an annulus chassis, a change
Diameter neck tube and one with the comb toothing match double-layer sealing structure；The first bleed hole is distributed in the annulus chassis；It is described
The caliber of variable diameter neck tube is connected to the inner wall end on the annulus chassis along seal closure axial direction gradual change, the big one end of caliber, and caliber is small
The other end be connected to the double-layer sealing structure；The double-layer sealing structure includes two parallel rings along the radial direction of seal closure
The width of shape wall, the first annular wall being connected with the variable diameter neck tube is greater than the second adjacent annular wall, the first annular wall
One end and second annular wall one end in the axial direction of seal closure be in same level, the other end of the first annular wall
Connected with the other end of second annular wall by a thin-walled rotary table, the comb toothing act on the first annular wall and
The second bleed is distributed in the inner wall of second annular wall, wall surface of the first annular wall close to thin-walled rotary table one end
Hole；The exterior panel and the inside panel be connected to the annulus chassis outer end wall and the thin-walled rotary table, the exterior panel
Stomatal limiting value tap air channel is drawn by the first bleed hole and second between the inside panel.
As above-mentioned composite material sealing cover, the first annular wall and second annular wall connect with the comb toothing
There is easily mill layer on the inner wall of touching；The material of the easy mill layer is one of elastic material or the resin containing inorganic filler；
If the material of above-mentioned composite material sealing cover, the easy mill layer is elastic material, wherein the elastic material is
Rubber.
If the material of above-mentioned composite material sealing cover, the easy mill layer is the resin of the filler containing object, wherein the nothing
Machine filler is one of talcum powder or graphite.
Such as above-mentioned composite material sealing cover, the seal closure has reinforcing rib structure；The section of the reinforcing rib is
One of " work " or " L " type；The material of the reinforcing rib is one of metal or composite material.
Such as above-mentioned composite material sealing cover, the reinforcing rib is arranged along the generatrix direction of the exterior panel, and along described
Seal closure is circumferentially equidistant symmetrical.
Such as above-mentioned composite material sealing cover, the reinforcing rib uses composite material, and the composite material is multiple using carbon fiber
Condensation material.
As the R angular zone of above-mentioned composite material sealing cover, the reinforcing rib is filled with unidirectional prepreg tape.
The above-mentioned composite material sealing cover for Aero-engine Bearing chamber is used to prepare the present invention also provides a kind of
Method, including, prepreg is made in bimaleimide resin sized glass fibres cloth by step a；Step b utilizes mold laying
The prepreg；Step c, to the prepreg molding after laying to obtain the inside panel of the seal closure and described outer
Siding；Step d forms the bleed hole on the inside panel.
Such as above-mentioned method, the step b includes, respectively on the mold of the mold of the inside panel and the exterior panel
Prepreg described in laying；The step c includes respectively to the prepreg and the exterior panel on the mold of the inside panel
Mold on the prepreg molding, with formed separation the inside panel and the exterior panel；The method also includes steps
Rapid e connects the inside panel and the exterior panel of separation.
Such as above-mentioned method, the step c includes being separately formed described in separation using autoclave or compression molding mode
Inside panel and the exterior panel.
Such as above-mentioned method, the step c is separately formed the isolated inside panel and institute using autoclave molding mode
State exterior panel；The method also includes pressurizeing to the prepreg after laying during executing the step b
Processing.
Such as above-mentioned method, the step b includes, in the public thin wall cavity mold of the inside panel and the exterior panel
Prepreg described in upper laying；The step c includes being integrally formed to the prepreg on the thin wall cavity mold, to be formed
The inside panel and exterior panel of one.
Such as above-mentioned method, the step c further includes, using autoclave or compression molding mode to the prepreg one
Molding, to form the inside panel and exterior panel of one.
Such as above-mentioned method, the step c is integrally formed the inside panel and exterior panel using autoclave molding mode；Institute
The method of stating further includes, and during executing the step b, carries out pressurized treatments to the prepreg after laying.
Such as above-mentioned method, the bleed hole includes the first bleed hole being formed on the inside panel, the step d packet
It includes and is machined first bleed hole on the inside panel after shaping.
Such as above-mentioned method, the bleed hole includes the second bleed hole being formed on the inside panel, the step d packet
It includes and is machined second bleed hole on the inside panel after shaping.
Such as above-mentioned method, the bleed hole includes the second bleed hole being formed on the inside panel, the step d packet
It includes during executing the step b, the desired location in second bleed hole carries out clip to the prepreg, is cut
The region of mouth forms second bleed hole after the inner wall sheet metal forming.
Such as above-mentioned method, the step b includes using quasi-isotropic laying, the prepreg to the prepreg
Laying along the mold circumferential subregion carry out；Top layer and lowest level in the laying, different zones it is described pre-
It is connected between leaching material using connecting method, the width of piece part is 0-2mm；In remaining each middle layer of the laying,
It is connected between the prepreg of different zones using overlapping mode, the width of overlap is 0-2mm；The laying middle layer
The overlap be circumferentially uniformly staggered 30 degree along the seal closure between adjacent layers；The top layer of the laying and most lower
The piece part of layer and the overlap of middle layer adjacent thereto are uniformly staggered 30 along the circumferential direction of the seal closure
Degree.
Such as above-mentioned method, the quasi-isotropic laying uses (0 °/45 °/- 45 °/90 °) 2s or (0 °/60 °/- 60 °)
One of 2s mode.
It further include that easily mill is formed in the mating surface that the seal closure is matched with the comb toothing such as above-mentioned method
Layer；The easy mill layer uses one of elastic material or the resin containing inorganic filler；The easy mill layer is along the seal closure
Circumferential subregion is fitted on the seal closure；Pressurized treatments are carried out to the easy mill layer.
Such as above-mentioned method, the easy mill layer uses the resin containing inorganic filler；The system of the resin containing inorganic filler
Preparation Method are as follows: add inorganic filler in resin, be dispersed with stirring the inorganic filler using ultrasonator, be then formed by curing
The resin containing inorganic filler；The inorganic filler uses one of talcum powder or graphite.
It further include forming reinforcing rib on the seal closure such as above-mentioned method；The section of the reinforcing rib be " work " or
One of " L " type；The reinforcing rib uses one of metal or composite material；The reinforcement is formed using pultrusion mode
Muscle.
Such as above-mentioned method, the reinforcing rib is arranged along the generatrix direction of the seal closure, and circumferential along the seal closure
It is equidistant symmetrical.
Such as above-mentioned method, the reinforcing rib uses composite material, and the composite material uses carbon-fiber composite material；Its
In, the reinforcing rib is formed using pultrusion mode, the 0 ° of directional spreding of the fiber of the carbon-fiber composite material along pultrusion.
Such as above-mentioned method, the reinforcing rib uses composite material, wherein forms the reinforcement using autoclave mode
Muscle.
Such as above-mentioned method, the R angular zone of Xiang Suoshu reinforcing rib fills unidirectional prepreg tape.
Detailed description of the invention
Fig. 1 shows the axis side view of composite material sealing cover of the present invention.
Fig. 2 shows the main views of composite material sealing cover of the present invention.
Fig. 3 shows the face composite material sealing cover A-A of the present invention cross-sectional view.
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.
Fig. 1 shows the axis side view of composite material sealing cover 100 of the present invention, as shown in Figure 1, composite material sealing cover
100 have ring structure, and intermediate circular hole portion is to by Aero-engine Bearing, composite material sealing cover 100 has and comb
The double-layer sealing structure 150 that toothing matches guarantees leakproofness.
Fig. 2 shows the main views of composite material sealing cover of the present invention, as shown in Fig. 2, the inner wall of composite material sealing cover
Be distributed with the first bleed hole 160 and bolt hole 180 on plate, bolt hole 180 to seal closure and Aero-engine Bearing chamber remaining
Used in component connection.
Fig. 3 shows the face composite material sealing cover A-A of the present invention cross-sectional view, as shown in figure 3, composite material sealing cover has
Inside panel 110 and exterior panel 120, inside panel 110 and exterior panel 120 are connected to region 130 and 140, seal closure and comb toothing
The contact surface matched is 154 parts, has the first bleed hole 160 and the second bleed hole 170 on inside panel, inside panel 110 with
Tap air channel is formed by the first bleed hole 160 and the second bleed hole 170 between exterior panel 120.
Inside panel 110 has class hubbed flange structure, including an annulus chassis, a variable diameter neck tube and one and comb toothing phase
The double-layer sealing structure 150 matched.The first bleed hole 160 is distributed in annulus chassis, and the caliber of variable diameter neck tube is axial gradually along seal closure
Become, the big one end of caliber is connected to the inner wall end on annulus chassis, and the small other end of caliber is connected to double-layer sealing structure 150.It is double
Layer sealing structure 150 includes two parallel annular walls, the first annular wall 151 being connected with variable diameter neck tube along the radial direction of seal closure
Width be greater than the second adjacent annular wall 152, one end of one end of first annular wall 151 and the second annular wall 152 is sealing
The axial direction of cover is in same level, and the other end of the other end of first annular wall 151 and the second annular wall 152 passes through a thin-walled
Rotary table 153 connects, and comb toothing acts on the inner wall of first annular wall 151 and the second annular wall 152, first annular wall 151
The second bleed hole 170 is distributed in wall surface close to 153 one end of thin-walled rotary table.
Composite material sealing cover provided by the invention is made of bimaleimide resin, bimaleimide resin
Oil resistant, high temperature resistance are excellent, can keep stablizing for a long time in 200 DEG C of oil and gas environments, can satisfy the operating condition of seal closure
Requirement.Compared with polyimide resin, bimaleimide resin mobility and mouldability are more preferable, and moulding process is more steady
It is fixed, it is released in forming process without low molecule by-product, the compact structure defect of molded article is few.
The present invention also provides a kind of methods of composite material sealing cover for being used to prepare Aero-engine Bearing chamber, including,
Prepreg is made in bimaleimide resin sized glass fibres cloth by step a, and preferably, plain weave can be used in glass fabric
Cloth, but not limited to this.In another embodiment, glass fabric uses satin.Step b, using mold laying prepreg,
Step c, the inside panel and exterior panel of seal closure are obtained to the prepreg molding after laying, and step d forms drawing on inside panel
Stomata.
The laying of prepreg is carried out along the circumferential subregion of mold, preferably, 3 is used in the laying of each layer of prepreg
The mode subregion that a sector laying combines carries out.Top layer and lowest level in siding laying, the prepreg of different zones
Between connected using connecting method, the width of piece part is 0-2mm；The overlap of laying middle layer edge between adjacent layers
Seal closure is circumferentially uniformly staggered 30 degree；The overlap joint of the top layer of laying and undermost piece part and middle layer adjacent thereto
Part is uniformly staggered 30 degree along the circumferential direction of seal closure, and the molded surface that siding may be implemented in such ply sequence is smooth, and transition is held
Easily, and guarantee to seal the uniformity of cover structure and the intensity of transitional region.
In one embodiment, quasi-isotropic symmetrical prepreg is used to the laying of seal closure inside panel and exterior panel,
Preferably, the mode of (0 °/45 °/- 45 °/90 °) 2s or (0 °/60 °/- 60 °) 2s be can choose, but not limited to this.
In one embodiment, the laying prepreg on the mold of the mold of inside panel and exterior panel respectively, preferably, siding
Laying use 24 layers of thickness in monolayer to carry out laying for the prepreg of 0.2mm, the wall panel thickness after laying is in 4-6mm.Step c packet
It includes and the prepreg on the mold of prepreg and exterior panel on the mold of inside panel is formed by compression molding mode respectively, with
Form isolated inside panel and exterior panel.Further include step e, connects the inside panel and exterior panel of separation.Inside panel and exterior panel
Pass through high temperature glue sticking in position 130 and 140 part of position.In another embodiment, inside panel and exterior panel are in 130 He of position
140 part of position is bolted by punching, and wherein screw hole connection uses counter sink, to guarantee that seal closure has a smooth surface transition.
In another embodiment, the laying prepreg on the mold of the mold of inside panel and exterior panel respectively, preferably, wall
The laying of plate uses 24 layers of thickness in monolayer to carry out laying for the prepreg of 0.2mm, and the wall panel thickness after laying is in 4-6mm.Step c
Including the prepreg on the mold respectively to prepreg and exterior panel on the mold of inside panel by autoclave molding mode at
Type, to form isolated inside panel and exterior panel.When by autoclave molding mode shaped inner plate and exterior panel, in laying wall
When the prepreg of plate, prepreg thickness often reaches 1mm or so, pressurized treatments is carried out to prepreg, preferably, in the every list of prepreg
Thickness degree is often plated in 4 layers of prepreg in 0.2mm, carries out pressurized treatments to it.In one embodiment, pressurized treatments include benefit
It is evacuated down to -0.1MPa, pressure maintaining 1min with vacuum pump, laying is compacted sufficiently bubble is discharged, improves the consistency of seal closure.Also
Including step e, the inside panel and exterior panel of separation are connected.Inside panel and exterior panel pass through height in position 130 and 140 part of position
Warm glue sticking.In another embodiment, inside panel and exterior panel are bolted in position 130 and 140 part of position by punching,
Wherein screw hole connection uses counter sink, to guarantee that seal closure has a smooth surface transition.
When being separately formed the inside panel and exterior panel of seal closure, inside panel by molding or autoclave molding method at
After type, machining is located at the first bleed hole 160 and the second bleed hole 170 on inside panel.Draw in first bleed hole 160 and second
The size of stomata 170 is set according to the demand of amount of air entrainment at bearing bore.In one embodiment, it is machined after interior wallboard forming
Bolt hole 180 on inside panel.In another embodiment, during prepreg is plated in, to the expected position of bolt hole 180
Then the prepreg clip set is placed bolt wherein, after to be formed, bolt, which is panelized, to be fixed in inside panel, by pre-
The mode buried processes the bolt hole 180 on inside panel.
In another embodiment, a thin wall cavity structure is formed first with the big engineering plastics of high temperature resistant, modulus to make
Preferably polyphenylene sulfide (PPS) or polyetherimide (PEI) material can be selected, but not limited to this for mold.In inside panel
It is plated in prepreg on the thin wall cavity mold public with exterior panel, the inside panel of seal closure is integrally formed using compression-moulding methods
And exterior panel.Thin wall cavity mold stays in seal closure as inner wall.
In another embodiment, a thin wall cavity structure is formed first with the big engineering plastics of high temperature resistant, modulus to make
Preferably polyphenylene sulfide (PPS) or polyetherimide (PEI) material can be selected, but not limited to this for mold.In inside panel
It is plated in prepreg on the thin wall cavity mold public with exterior panel, the inner wall of seal closure is integrally formed using autoclave molding method
Plate and exterior panel.Thin wall cavity mold stays in seal closure as inner wall.Seal closure is integrally formed by autoclave molding mode
Inside panel and exterior panel when, in the prepreg of laying siding, prepreg thickness often reaches 1mm or so, to prepreg carry out
Pressurized treatments preferably in the every thickness in monolayer of prepreg in 0.2mm, are often plated in 4 layers of prepreg, carry out pressurized treatments to it.
In one embodiment, pressurized treatments are evacuated down to -0.1MPa, pressure maintaining 1min including the use of vacuum pump, are compacted laying sufficiently to arrange
Bubble out improves the consistency of seal closure.
When being integrally formed the inside panel and exterior panel of seal closure, during prepreg is plated in, in the second bleed hole 170
Desired location to prepreg carry out clip, the second bleed hole is formed after interior wallboard forming by the region of clip.In seal closure
Inside panel and after exterior panel is integrally formed, be machined the first bleed hole 160 and bolt hole 180.First bleed hole, 160 He
The size in the second bleed hole 170 is set according to the demand of amount of air entrainment at bearing bore.
In one embodiment, the first annular wall 151 of double-layer sealing structure 150 and the second annular wall 152 and comb toothing
The surface matched is provided with easily mill layer 154, and easily grinding layer 154 can select elastic material, preferably, can select rubber, but
It is not limited.Easily grind the first annular wall that layer 154 is fitted in the inside panel 110 of seal closure along the circumferential subregion of seal closure
151 and second in annular wall 152, preferably, can be classified as four 90 ° of half ring regions and be fitted in respectively with the mode of gluing
On first annular wall 151 and the second annular wall 152.In one embodiment, easily mill layer 154 with a thickness of 2.5-3mm.It is being bonded
When easily grinding layer 154.Pressurized treatments are carried out to easy mill 154 region of layer.Preferably, it can use the mode of vacuum bag pressure to easy mill layer
154 pressurize, evacuated pressure to -0.095MPa, and for pressure maintaining 1min so that the fitting of easily mill layer 154 is more fine and close, reduction is easy
Grind the porosity in 154 region of layer.
In another embodiment, easily mill layer 154 selects the resin containing inorganic filler to be made, and preferably, inorganic filler is optional
With talcum powder or graphite, but not limited to this.By inorganic filler addition in resin, it is dispersed with stirring using ultrasonator, Gu
After change formed easily mill layer 154, then by its along the circumferential subregion of seal closure be fitted in seal closure inside panel 110 it is first annular
On wall 151 and the second annular wall 152, preferably, four 90 ° of half ring regions can be classified as and be bonded respectively with the mode of gluing
On first annular wall 151 and the second annular wall 152.In one embodiment, easily mill layer 154 with a thickness of 2.5-3mm.It is pasting
When closing easily mill layer 154.Pressurized treatments are carried out to easy mill 154 region of layer.Preferably, it can use the mode of vacuum bag pressure to easy mill
Layer 154 pressurizes, evacuated pressure to -0.095MPa, and pressure maintaining 1min is reduced so that the fitting of easily mill layer 154 is more fine and close
The easily porosity in mill 154 region of layer.
In one embodiment, it is provided with reinforcing rib structure on seal closure exterior panel, is reduced in seal closure wall panel thickness, knot
In the case where structure loss of weight, cooperates with seal closure and increase siding rigidity.The section of reinforcing rib is one of " work " or " L " type, is adopted
With metal or composite material, it is arranged along the generatrix direction of exterior panel, and circumferentially equidistant symmetrical along seal closure, can increasing
Guarantee the uniformity and balance of sealing cover structure while strong seal closure structural rigidity.Preferably, setting 4 may be selected along close
Circumferential 90 ° equidistant symmetrical reinforcing ribs of sealing cover.
In one embodiment, reinforcing rib material selection composite material preferably selects carbon-fiber composite material, but not with this
It is limited.Reinforcing rib is formed using pultrude process, reinforcing rib may be implemented along 0 ° of directional spreding of pultrusion in the fiber of composite material
The maximum bending resistance efficiency of structure, and allow continuous production.In another embodiment, using autoclave process to reinforcing rib
Molding.
In one embodiment, it is filled using R angular zone of the unidirectional prepreg tape to reinforcing rib, so that the R of reinforcing rib
Angle weakness zone is strengthened, and the anti-bending strength of reinforcing rib is more excellent.
Composite material sealing cover density according to made of the above method for Aero-engine Bearing chamber can satisfy close
The working environment of sealing cover high temperature, oil resistant, and realize the loss of weight of engine.Meanwhile using seal closure made of the above method,
Its hole is smaller, and intensity and quality can be guaranteed.
Embodiment described above is only technical idea and feature to illustrate the invention, and purpose makes to be familiar with this technology
Field person cans understand the content of the present invention and implement it accordingly, when cannot with restriction the scope of the patents of the invention, i.e. Fan Yiben
Equivalent change or modification made by revealed spirit are invented, should be covered in the scope of the patents of the invention.
Claims (28)
1. a kind of method for preparing composite material sealing cover, the seal closure is matched with a comb toothing to form sealing knot
Structure, the seal closure includes inside panel and exterior panel, by the inside panel between the inside panel and the exterior panel
Draw stomatal limiting value tap air channel, which comprises
Prepreg is made in bimaleimide resin sized glass fibres cloth by step a；
Step b utilizes prepreg described in mold laying；
Step c obtains the inside panel and the exterior panel of the seal closure to the prepreg molding after laying；
Step d forms the bleed hole on the inside panel.
2. the method as described in claim 1, which is characterized in that the step b includes, respectively in the mold of the inside panel and
Prepreg described in laying on the mold of the exterior panel；
The step c includes respectively to the institute on the mold of the prepreg and the exterior panel on the mold of the inside panel
Prepreg molding is stated, to form the inside panel and the exterior panel of separation；
The method also includes step e, connect the inside panel and the exterior panel of separation.
3. method according to claim 2, which is characterized in that the step c includes, using autoclave or compression molding mode
It is separately formed the inside panel and the exterior panel of separation.
4. method as claimed in claim 3, which is characterized in that the step c is separately formed institute using autoclave molding mode
State the inside panel and the exterior panel of separation；
The method also includes carrying out pressurized treatments to the prepreg after laying during executing the step b.
5. the method as described in claim 1, which is characterized in that the step b includes, in the inside panel and the exterior panel
Prepreg described in laying on public thin wall cavity mold；
The step c includes being integrally formed to the prepreg on the thin wall cavity mold, to form the described interior of one
Siding and exterior panel.
6. method as claimed in claim 5, which is characterized in that the step c further includes, using autoclave or compression molding side
Formula is integrally formed the prepreg, to form the inside panel and exterior panel of one.
7. method as claimed in claim 6, which is characterized in that the step c is integrally formed institute using autoclave molding mode
State inside panel and exterior panel；
The method also includes carrying out pressurized treatments to the prepreg after laying during executing the step b.
8. the method as described in claim 1, which is characterized in that the bleed hole includes first be formed on the inside panel
Bleed hole, the step d include that first bleed hole is machined on the inside panel after molding.
9. method according to claim 2, which is characterized in that the bleed hole includes second be formed on the inside panel
Bleed hole, the step d include that second bleed hole is machined on the inside panel after molding.
10. method as claimed in claim 5, which is characterized in that the bleed hole includes be formed on the inside panel
Two bleed holes, the step d is included in execute the step b during, second bleed hole desired location to institute
It states prepreg and carries out clip, second bleed hole is formed after the inner wall sheet metal forming by the region of clip.
11. the method as described in claim 1, which is characterized in that the step b includes, to the prepreg using it is quasi- respectively to
The laying of same sex laying, the prepreg is carried out along the circumferential subregion of the mold；
Top layer and lowest level in the laying are connected between the prepreg of different zones, piece using connecting method
Partial width is 0-2mm；
It is connected, is taken using overlapping mode between remaining each middle layer of the laying, the prepreg of different zones
The width of socket part point is 0-2mm；
The overlap of the laying middle layer is circumferentially uniformly staggered 30 degree along the seal closure between adjacent layers；
The overlap edge of the top layer of the laying and the undermost piece part and middle layer adjacent thereto
The circumferential direction of the seal closure is uniformly staggered 30 degree.
12. method as claimed in claim 11, which is characterized in that the quasi-isotropic laying using (0 °/45 °/- 45 °/
90 °) one of 2s or (0 °/60 °/- 60 °) 2s mode.
13. the method as described in claim 1, which is characterized in that further include matching in the seal closure and the comb toothing
Easily mill layer is formed in the mating surface of conjunction；
The easy mill layer uses one of elastic material or the resin containing inorganic filler；
The easy mill layer is fitted on the seal closure along the circumferential subregion of the seal closure；
Pressurized treatments are carried out to the easy mill layer.
14. method as claimed in claim 13, which is characterized in that the easy mill layer uses the resin containing inorganic filler；
The resin containing inorganic filler the preparation method comprises the following steps: add inorganic filler in resin, stirred using ultrasonator
Disperse the inorganic filler, is then formed by curing the resin containing inorganic filler；
The inorganic filler uses one of talcum powder or graphite.
15. the method as described in claim 1, which is characterized in that further include forming reinforcing rib on the seal closure；
The section of the reinforcing rib is one of " work " or " L " type；
The reinforcing rib uses one of metal or composite material；
The reinforcing rib is formed using pultrusion mode.
16. method as claimed in claim 15, which is characterized in that the reinforcing rib is set along the generatrix direction of the seal closure
It sets, and circumferentially equidistant symmetrical along the seal closure.
17. method as claimed in claim 15, which is characterized in that the reinforcing rib uses composite material, the composite material
Using carbon-fiber composite material；
Wherein, the reinforcing rib is formed using pultrusion mode, the 0 ° of directional spreding of the fiber of the carbon-fiber composite material along pultrusion.
18. method as claimed in claim 15, which is characterized in that the reinforcing rib uses composite material, wherein use hot pressing
Tank mode forms the reinforcing rib.
19. method as claimed in claim 15, which is characterized in that the R angular zone of Xiang Suoshu reinforcing rib fills unidirectional preimpregnation
Band.
20. the composite material sealing cover of Aero-engine Bearing chamber is used for made of a kind of basis method as described in claim 1,
The seal closure is matched with a comb toothing to form sealing structure, and the seal closure includes inside panel and exterior panel, described
By drawing stomatal limiting value tap air channel on the inside panel between inside panel and the exterior panel, the composite material is using double
Maleimide resin and glass fabric material.
21. composite material sealing cover as claimed in claim 20, which is characterized in that the inside panel is class hubbed flange knot
Structure, the double-layer sealing structure to match including an annulus chassis, a variable diameter neck tube and one and the comb toothing；
The first bleed hole is distributed in the annulus chassis；
The caliber of the variable diameter neck tube is connected to the inner wall on the annulus chassis along seal closure axial direction gradual change, the big one end of caliber
End, the small other end of caliber are connected to the double-layer sealing structure；
The double-layer sealing structure includes two parallel annular walls along the radial direction of seal closure, to be connected with the variable diameter neck tube
The width of one annular wall is greater than the second adjacent annular wall, and one end and second annular wall one end of the first annular wall exist
The axial direction of seal closure is in same level, and the other end of the other end of the first annular wall and second annular wall passes through
The connection of one thin-walled rotary table, the comb toothing acts on the inner wall of the first annular wall and second annular wall, described
The second bleed hole is distributed in wall surface of the first annular wall close to thin-walled rotary table one end；
The exterior panel and the inside panel be connected to the annulus chassis outer end wall and the thin-walled rotary table, the exterior panel
Stomatal limiting value tap air channel is drawn by the first bleed hole and second between the inside panel.
22. composite material sealing cover as claimed in claim 21, which is characterized in that the first annular wall and second ring
There is easily mill layer on the inner wall that shape wall is contacted with the comb toothing；
The material of the easy mill layer is one of elastic material or the resin containing inorganic filler.
23. composite material sealing cover as claimed in claim 22, which is characterized in that the material of the easy mill layer is elastic material
Material, wherein the elastic material is rubber.
24. composite material sealing cover as claimed in claim 22, which is characterized in that the material of the easy mill layer is to fill out containing object
The resin of material, wherein the inorganic filler is one of talcum powder or graphite.
25. composite material sealing cover as claimed in claim 21, which is characterized in that the seal closure has reinforcing rib structure,
The section of the reinforcing rib is one of " work " or " L " type, and the material of the reinforcing rib is one in metal or composite material
Person.
26. composite material sealing cover as claimed in claim 25, which is characterized in that mother of the reinforcing rib along the exterior panel
The setting of line direction, and it is circumferentially equidistant symmetrical along the seal closure.
27. composite material sealing cover as claimed in claim 25, which is characterized in that the reinforcing rib uses composite material, institute
Composite material is stated using carbon-fiber composite material.
28. composite material sealing cover as claimed in claim 25, which is characterized in that the R angular zone of the reinforcing rib is filled with
Unidirectional prepreg tape.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112984555A (en) * | 2021-04-14 | 2021-06-18 | 中国航发上海商用航空发动机制造有限责任公司 | Workpiece protection method, machining method and workpiece |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5330324A (en) * | 1992-09-09 | 1994-07-19 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Annular gasket disposed at one axial extremity of a rotor and covering blade feet |
| CN102196898A (en) * | 2008-10-22 | 2011-09-21 | 塞特克技术公司 | Improved processing of polymer matrix composites |
| JP5017699B2 (en) * | 2006-02-15 | 2012-09-05 | 綜研化学株式会社 | Resin composition for molding polyamideimide resin and molded article thereof |
| CN203499731U (en) * | 2013-09-03 | 2014-03-26 | 中国航空工业集团公司沈阳发动机设计研究所 | High-temperature and high-speed floating ring air film sealing structure |
| CN104929779A (en) * | 2015-04-30 | 2015-09-23 | 中国科学院工程热物理研究所 | Turbine disk connecting structure and gas turbine engine with same |
| CN105240535A (en) * | 2015-09-17 | 2016-01-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Bearing sealing device |
| CN105402028A (en) * | 2015-04-30 | 2016-03-16 | 中国科学院工程热物理研究所 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
| JP2016142267A (en) * | 2015-02-03 | 2016-08-08 | ゼネラル・エレクトリック・カンパニイ | Cmc turbine components and methods of forming cmc turbine components |
| CN205910008U (en) * | 2016-08-02 | 2017-01-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Load frame behind turbine of area cooling bleed |
| CN106677904A (en) * | 2016-12-29 | 2017-05-17 | 中国科学院工程热物理研究所 | Adjustable pad structure used in high-temperature side bearing cavity of engine |
-
2017
- 2017-09-27 CN CN201710890126.4A patent/CN109555603B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5330324A (en) * | 1992-09-09 | 1994-07-19 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Annular gasket disposed at one axial extremity of a rotor and covering blade feet |
| JP5017699B2 (en) * | 2006-02-15 | 2012-09-05 | 綜研化学株式会社 | Resin composition for molding polyamideimide resin and molded article thereof |
| CN102196898A (en) * | 2008-10-22 | 2011-09-21 | 塞特克技术公司 | Improved processing of polymer matrix composites |
| CN203499731U (en) * | 2013-09-03 | 2014-03-26 | 中国航空工业集团公司沈阳发动机设计研究所 | High-temperature and high-speed floating ring air film sealing structure |
| JP2016142267A (en) * | 2015-02-03 | 2016-08-08 | ゼネラル・エレクトリック・カンパニイ | Cmc turbine components and methods of forming cmc turbine components |
| CN104929779A (en) * | 2015-04-30 | 2015-09-23 | 中国科学院工程热物理研究所 | Turbine disk connecting structure and gas turbine engine with same |
| CN105402028A (en) * | 2015-04-30 | 2016-03-16 | 中国科学院工程热物理研究所 | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine |
| CN105240535A (en) * | 2015-09-17 | 2016-01-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Bearing sealing device |
| CN205910008U (en) * | 2016-08-02 | 2017-01-25 | 中国航空工业集团公司沈阳发动机设计研究所 | Load frame behind turbine of area cooling bleed |
| CN106677904A (en) * | 2016-12-29 | 2017-05-17 | 中国科学院工程热物理研究所 | Adjustable pad structure used in high-temperature side bearing cavity of engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112984555A (en) * | 2021-04-14 | 2021-06-18 | 中国航发上海商用航空发动机制造有限责任公司 | Workpiece protection method, machining method and workpiece |
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| Publication number | Publication date |
|---|---|
| CN109555603B (en) | 2020-01-10 |
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