CN109555603B - Composite material sealing cover and preparation method thereof - Google Patents
Composite material sealing cover and preparation method thereof Download PDFInfo
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- CN109555603B CN109555603B CN201710890126.4A CN201710890126A CN109555603B CN 109555603 B CN109555603 B CN 109555603B CN 201710890126 A CN201710890126 A CN 201710890126A CN 109555603 B CN109555603 B CN 109555603B
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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
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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
- B29C70/54—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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- 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 invention provides a composite material sealing cover which is used for being matched with a grate structure to form a sealing structure and comprises an inner wall plate and an outer wall plate, an air entraining channel is formed between the inner wall plate and the outer wall plate through an air entraining hole in the inner wall plate, and the composite material is made of bismaleimide resin and glass fiber cloth. The invention also provides a method for preparing the composite material sealing cover, which specifically comprises the following steps: step a, impregnating a glass fiber cloth with bismaleimide resin to prepare a prepreg; b, laying the prepreg by using a mould; c, molding the laid prepreg to obtain the inner wall plate and the outer wall plate of the sealing cover, and d, forming the air guide holes in the inner wall plate.
Description
Technical Field
The invention relates to a composite material sealing cover and a preparation method thereof, in particular to an oil-resistant high-temperature-resistant composite material sealing cover for an aeroengine bearing cavity and a preparation method thereof.
Background
In the transmission structure of the mechanical system of the aircraft engine, in order to avoid oil gas in the bearing cavity from leaking out of the bearing cavity, sealing structures are arranged at the front and the back of the bearing cavity, the current application is mature, a comb tooth structure is adopted, a part matched with the comb tooth sealing structure is a sealing cover, and the working environment of the sealing cover requires that the material of the sealing cover has high temperature resistance, generally 200 ℃ resistance, oil resistance and certain strength.
At present, all sealing covers of bearing cavities of domestic aero-engines are made of metal materials, the traditional sealing covers made of metal materials are high in density, the weight of the aero-engines cannot be reduced, and the aims of high efficiency and low oil consumption of the aero-engines cannot be fulfilled. The foreign organic type adopts glass fiber reinforced polyimide to manufacture the formed composite material sealing cover, and although the glass fiber reinforced polyimide has low density and good high temperature resistance and oil resistance, the polyimide has high cost, difficult dissolution and infusibility, poor stability of the forming process and difficult control of the forming process. In addition, in the preparation process of the glass fiber reinforced polyimide prepreg, the solvent is difficult to volatilize completely, the residual solvent is released during the molding of the composite material, so that pores are generated in a product, and the strength and the quality of the product are influenced to a certain extent.
Therefore, a composite material sealing cover which can meet the sealing performance, high temperature resistance, oil resistance and strength characteristics of the aeroengine bearing cavity sealing ring and can be conveniently realized by adopting a composite material manufacturing process is needed.
Disclosure of Invention
The invention aims to provide a composite material sealing cover for an aeroengine bearing cavity, which has low density, high temperature resistance, oil resistance and certain strength, is used for forming a sealing structure by matching with a labyrinth structure, realizes the sealing performance, improves the efficiency of the aeroengine and reduces the oil consumption. The invention also aims to provide a preparation method of the composite material sealing cover.
In order to achieve the purpose, the composite material sealing cover for the bearing cavity of the aircraft engine provided by the invention is matched with a labyrinth structure to form a sealing structure, the sealing cover comprises an inner wall plate and an outer wall plate, an air entraining channel is formed between the inner wall plate and the outer wall plate through an air entraining hole in the inner wall plate, and the composite material is made of bismaleimide resin and glass fiber cloth.
According to the composite material sealing cover, the inner wall plate is of a similar necked flange structure and comprises a circular ring chassis, a reducing neck pipe and a double-layer sealing structure matched with the grate structure; a first air guide hole is distributed on the circular ring base plate; the pipe diameter of the reducing neck pipe gradually changes along the axial direction of the sealing cover, one end with the large pipe diameter is connected to the inner wall end of the circular ring chassis, and the other end with the small pipe diameter is connected to the double-layer sealing structure; the double-layer sealing structure comprises two parallel annular walls along the radial direction of the sealing cover, the width of a first annular wall connected with the reducing neck pipe is larger than that of an adjacent second annular wall, one end of the first annular wall and one end of the second annular wall are positioned on the same horizontal plane in the axial direction of the sealing cover, the other end of the first annular wall is connected with the other end of the second annular wall through a thin-wall circular truncated cone, the grate structure acts on the inner wall surfaces of the first annular wall and the second annular wall, and second air guide holes are distributed on the wall surface of the first annular wall close to one end of the thin-wall circular truncated cone; the outer wall plate and the inner wall plate are connected to the outer end wall of the circular ring chassis and the thin-wall circular truncated cone, and an air entraining channel is formed between the outer wall plate and the inner wall plate through a first air entraining hole and a second air entraining hole.
The composite material sealing cover is characterized in that the inner wall surfaces of the first annular wall and the second annular wall, which are in contact with the grate tooth structure, are provided with the easily-ground layers; the material of the easily-abraded layer is one of elastic material or resin containing inorganic filler;
in the composite material sealing cover, the material of the easily-abraded layer is an elastic material, wherein the elastic material is rubber.
In the composite material sealing cover, the material of the easily-abraded layer is resin containing object filler, wherein the inorganic filler is one of talcum powder or graphite.
A composite material containment cap as described above, said containment cap having a stiffener structure; the section of the reinforcing rib is in one of I shape or L shape; the material of the reinforcing rib is one of metal or composite material.
According to the composite material sealing cover, the reinforcing ribs are arranged along the bus direction of the outer wall plate and are distributed along the circumferential direction of the sealing cover in an equidistant and symmetrical mode.
According to the composite material sealing cover, the reinforcing ribs are made of composite materials, and the composite materials are made of carbon fiber composite materials.
As with the composite closure described above, the R-corner regions of the ribs are filled with unidirectional prepreg tape.
The invention also provides a method for preparing the composite material sealing cover for the bearing cavity of the aeroengine, which comprises the following steps of a, preparing bismaleimide resin impregnated glass fiber cloth into prepreg; b, laying the prepreg by using a mould; c, molding the laid prepreg to obtain the inner wall plate and the outer wall plate of the sealing cover; and d, forming the air guide holes on the inner wall plate.
In the method, the step b comprises laying up the prepreg on the mold of the inner wall plate and the mold of the outer wall plate respectively; the step c comprises respectively molding the prepreg on the mold of the inner wall plate and the prepreg on the mold of the outer wall plate to form the inner wall plate and the outer wall plate which are separated; the method further comprises a step e of connecting the separated inner and outer wall panels.
In the above method, the step c includes forming the separated inner wall plate and the outer wall plate separately by using an autoclave or a compression molding method.
In the above method, in the step c, the separated inner wall plate and the outer wall plate are respectively formed by adopting an autoclave forming mode; the method also comprises the step of pressurizing the laminated prepreg in the process of executing the step b.
In the method, step b comprises laying up the prepreg on a thin-walled cavity mould common to the inner and outer wall panels; and the step c comprises integrally molding the prepreg on the thin-wall cavity mold to form the integrated inner wall plate and outer wall plate.
In the above method, step c further includes integrally molding the prepreg by autoclave or compression molding to form the integrated inner and outer wall panels.
In the above method, in the step c, the inner wall plate and the outer wall plate are integrally formed by adopting an autoclave forming mode; the method also comprises the step of pressurizing the laminated prepreg in the process of executing the step b.
In the method, the bleed air holes include first bleed air holes formed in the inner wall panel, and the step d includes machining the first bleed air holes in the formed inner wall panel.
In the method, the bleed air holes include second bleed air holes formed in the inner wall panel, and the step d includes machining the second bleed air holes in the formed inner wall panel.
In the method as described above, the air-guiding holes include second air-guiding holes formed in the inner wall panel, and the step d includes cutting the prepreg at a desired position of the second air-guiding holes during the step b, wherein the cut area forms the second air-guiding holes after the inner wall panel is formed.
According to the method, the step b comprises the steps of carrying out quasi-isotropic laying on the prepreg, wherein the laying of the prepreg is carried out in a circumferential subarea manner along the mold; connecting the prepregs in different areas on the uppermost layer and the lowermost layer of the paving layer in a splicing mode, wherein the width of a splicing seam part is 0-2 mm; connecting the prepregs in different areas of each of the rest intermediate layers of the paving layer in an overlapping manner, wherein the width of the overlapping part is 0-2 mm; the lap joint parts of the ply intermediate layers are staggered by 30 degrees uniformly along the circumferential direction of the seal cover between adjacent layers; the splicing seam parts of the uppermost layer and the lowermost layer of the layer and the lap joint parts of the middle layer adjacent to the splicing seam parts are staggered by 30 degrees uniformly along the circumferential direction of the sealing cover.
In the above method, the quasi-isotropic ply is one of (0 °/45 °/90 °) for 2s or (0 °/60 °) for 2 s.
The method further comprises the step of forming an easily-abraded layer on the matching surface of the sealing cover and the grate structure; the easily-abraded layer is made of one of elastic materials or resins containing inorganic fillers; the easily-abraded layer is attached to the sealing cover in a partitioned mode along the circumferential direction of the sealing cover; and carrying out pressurization treatment on the easily-abraded layer.
In the above method, the easily-abraded layer is made of resin containing inorganic filler; the preparation method of the resin containing the inorganic filler comprises the following steps: adding an inorganic filler into resin, stirring and dispersing the inorganic filler by using an ultrasonic oscillator, and then curing to form the resin containing the inorganic filler; the inorganic filler is one of talcum powder or graphite.
The method as described above, further comprising forming a bead on the seal cap; the section of the reinforcing rib is in one of I shape or L shape; the reinforcing rib is made of one of metal or composite material; and forming the reinforcing rib in a pultrusion mode.
According to the method, the reinforcing ribs are arranged along the generatrix direction of the seal cover and are equidistantly and symmetrically distributed along the circumferential direction of the seal cover.
According to the method, the reinforcing rib is made of a composite material, and the composite material is made of a carbon fiber composite material; the reinforcing rib is formed by pultrusion, and fibers of the carbon fiber composite material are distributed along the pultrusion direction of 0 degree.
In the method, the reinforcing rib is made of composite materials, wherein the reinforcing rib is formed in an autoclave mode.
In the above method, the unidirectional prepreg tape is filled into the R-angle region of the reinforcing bead.
Drawings
FIG. 1 shows an isometric view of a composite seal boot of the present invention.
FIG. 2 shows a front view of the composite seal housing of the present invention.
Figure 3 shows a cross-sectional view of a-a of the composite material boot seal of the present invention.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments. It is noted that the aspects described below in connection with the figures and the specific embodiments are only exemplary and should not be construed as imposing any limitation on the scope of the present invention.
Fig. 1 shows an axial side view of a composite material seal housing 100 according to the present invention, as shown in fig. 1, the composite material seal housing 100 has an annular configuration with a central circular bore portion for passage of an aircraft engine bearing, and the composite material seal housing 100 has a double seal 150 for sealing engagement with a labyrinth arrangement.
Fig. 2 shows a front view of the composite material sealing cap according to the invention, and as shown in fig. 2, a first air guiding hole 160 and a bolt hole 180 are distributed on an inner wall plate of the composite material sealing cap, and the bolt hole 180 is used for connecting the sealing cap with the rest parts of the bearing cavity of the aeroengine.
FIG. 3 shows a cross-sectional view of the composite sealing cap A-A of the present invention, as shown in FIG. 3, the composite sealing cap has an inner wall plate 110 and an outer wall plate 120, the inner wall plate 110 and the outer wall plate 120 are connected to the areas 130 and 140, the contact surface of the sealing cap with the labyrinth structure is part 154, the inner wall plate has a first air bleed hole 160 and a second air bleed hole 170, and a bleed air passage is formed between the inner wall plate 110 and the outer wall plate 120 through the first air bleed hole 160 and the second air bleed hole 170.
The inner wall plate 110 has a neck-like flange structure, including a circular base plate, a reducing neck tube and a double-layer sealing structure 150 matching with the grate structure. First air guide holes 160 are distributed on the circular ring chassis, the pipe diameter of the reducing neck pipe is gradually changed along the axial direction of the sealing cover, one end with a large pipe diameter is connected to the inner wall end of the circular ring chassis, and the other end with a small pipe diameter is connected to the double-layer sealing structure 150. The double-layer sealing structure 150 comprises two parallel annular walls along the radial direction of the sealing cover, the width of a first annular wall 151 connected with the reducing neck pipe is larger than that of an adjacent second annular wall 152, one end of the first annular wall 151 and one end of the second annular wall 152 are located on the same horizontal plane in the axial direction of the sealing cover, the other end of the first annular wall 151 and the other end of the second annular wall 152 are connected through a thin-wall circular truncated cone 153, a labyrinth structure acts on the inner wall surfaces of the first annular wall 151 and the second annular wall 152, and second air guide holes 170 are distributed on the wall surface of one end, close to the thin-wall circular truncated cone 153, of the first annular wall 151.
The composite material sealing cover provided by the invention is made of bismaleimide resin, the bismaleimide resin has excellent oil resistance and high temperature resistance, can be kept stable in an oil-gas environment at 200 ℃ for a long time, and can meet the working condition use requirement of the sealing cover. Compared with polyimide resin, the bismaleimide resin has better fluidity and moldability, more stable molding process, no low molecular by-product emission in the molding process, and less compact structure defects of molded parts.
The invention also provides a method for preparing the composite material sealing cover of the bearing cavity of the aeroengine, which comprises the step a of preparing the bismaleimide resin impregnated glass fiber cloth into a prepreg, preferably, the glass fiber cloth can adopt plain cloth, but not limited to. In another embodiment, the glass fiber cloth is satin cloth. B, laying a prepreg by using a mould, c, forming the laid prepreg to obtain an inner wall plate and an outer wall plate of the sealing cover, and d, forming air guide holes on the inner wall plate.
The laying of the prepreg is performed in regions along the circumferential direction of the mold, preferably, the laying of each layer of prepreg is performed in regions by adopting a mode of combining 3 fan-shaped laying layers. Connecting the prepregs in different areas on the uppermost layer and the lowermost layer of the wall plate laying layer in a splicing mode, wherein the width of a splicing seam part is 0-2 mm; the lap joint parts of the ply intermediate layers are uniformly staggered by 30 degrees along the circumferential direction of the sealing cover between the adjacent layers; the splicing seam parts of the uppermost layer and the lowermost layer of the laying layer and the lap joint part of the middle layer adjacent to the splicing seam parts are staggered by 30 degrees uniformly along the circumferential direction of the sealing cover, the forming surface of the wall plate can be smooth in the laying mode, the transition is easy, and the uniformity of the structure of the sealing cover and the strength of a transition area are ensured.
In one embodiment, a quasi-isotropic symmetrical prepreg is used for the lay-up of the inner and outer wall panels of the sealed enclosure, preferably (0 °/45 °/90 °)2s or (0 °/60 °)2s, but not limited thereto.
In one embodiment, the prepreg is laid on the mould of the inner wall plate and the mould of the outer wall plate respectively, preferably, the ply of the wall plate is laid by adopting 24 layers of single-layer prepreg with the thickness of 0.2mm, and the thickness of the wall plate after ply is 4-6 mm. And c, respectively molding the prepreg on the mold of the inner wall plate and the prepreg on the mold of the outer wall plate by a compression molding mode to form the separated inner wall plate and the separated outer wall plate. And e, connecting the separated inner wall plate and the outer wall plate. The inner and outer wall panels are partially bonded by high temperature glue at locations 130 and 140. In another embodiment, the inner and outer wall panels are partially bolted at locations 130 and 140 by a hole-punched bolt, wherein the hole-punched connection is countersunk to ensure a smooth transition of the surface of the enclosure.
In another embodiment, the prepreg is respectively paved on the die of the inner wall plate and the die of the outer wall plate, preferably, the paving layer of the wall plate is paved by adopting 24 layers of single-layer prepreg with the thickness of 0.2mm, and the thickness of the wall plate after paving is 4-6 mm. And c, respectively forming the prepreg on the die of the inner wall plate and the prepreg on the die of the outer wall plate in an autoclave forming mode to form the separated inner wall plate and the outer wall plate. When the inner wall plate and the outer wall plate are molded in an autoclave molding mode, when the prepreg of the wall plate is laid, the prepreg is pressurized when the thickness of the prepreg reaches about 1mm, and preferably, when the thickness of each single layer of the prepreg is 0.2mm, 4 layers of prepreg are laid and pressurized. In one embodiment, the pressurizing treatment comprises the steps of utilizing a vacuum pump to vacuumize to-0.1 MPa, maintaining the pressure for 1min, fully compacting the layering to exhaust air bubbles, and improving the compactness of the sealing cover. And e, connecting the separated inner wall plate and the outer wall plate. The inner and outer wall panels are partially bonded by high temperature glue at locations 130 and 140. In another embodiment, the inner and outer wall panels are partially bolted at locations 130 and 140 by a hole-punched bolt, wherein the hole-punched connection is countersunk to ensure a smooth transition of the surface of the enclosure.
When the inner and outer wall panels of the closure cap are separately formed, the first and second air guide holes 160 and 170 are machined in the inner wall panel after the inner wall panel is formed by a molding or autoclave molding method. The first bleed holes 160 and the second bleed holes 170 are sized according to the bleed air volume requirement at the bearing cavity. In one embodiment, the bolt holes 180 on the inner wall panel are machined after the inner wall panel is formed. In another embodiment, during the prepreg laying process, the prepreg is cut at the desired position of the bolt hole 180, then the bolt is placed in the prepreg, after molding, the bolt is embedded and fixed in the inner wall plate, and the bolt hole 180 on the inner wall plate is processed by pre-embedding.
In another embodiment, a thin-walled cavity structure is formed by using a high-temperature-resistant and high-modulus engineering plastic as a mold, preferably, polyphenylene sulfide (PPS) or Polyetherimide (PEI) material is used, but not limited thereto. And (3) paving prepreg on a common thin-wall cavity mould of the inner wall plate and the outer wall plate, and integrally forming the inner wall plate and the outer wall plate of the sealing cover by adopting a compression molding method. The thin-walled cavity mold remains as an inner wall in the sealing boot.
In another embodiment, a thin-walled cavity structure is formed by using a high-temperature-resistant and high-modulus engineering plastic as a mold, preferably, polyphenylene sulfide (PPS) or Polyetherimide (PEI) material is used, but not limited thereto. And (3) paving prepreg on a common thin-wall cavity mould of the inner wall plate and the outer wall plate, and integrally forming the inner wall plate and the outer wall plate of the sealing cover by adopting an autoclave forming method. The thin-walled cavity mold remains as an inner wall in the sealing boot. When the inner wall plate and the outer wall plate of the sealing cover are integrally formed in an autoclave forming mode, when the prepreg of the wall plate is laid, the prepreg is subjected to pressurization treatment when the thickness of the prepreg reaches about 1mm, and preferably, when the thickness of each single layer of the prepreg is 0.2mm, 4 layers of prepreg are laid and subjected to pressurization treatment. In one embodiment, the pressurizing treatment comprises the steps of utilizing a vacuum pump to vacuumize to-0.1 MPa, maintaining the pressure for 1min, fully compacting the layering to exhaust air bubbles, and improving the compactness of the sealing cover.
When the inner wall plate and the outer wall plate of the sealing cover are integrally formed, the prepreg is cut at a desired position of the second air guiding hole 170 in the prepreg laying process, and the cut area forms the second air guiding hole after the inner wall plate is formed. After the inner and outer wall plates of the sealing cap are integrally formed, the first air guide holes 160 and the bolt holes 180 are machined. The first bleed holes 160 and the second bleed holes 170 are sized according to the bleed air volume requirement at the bearing cavity.
In an embodiment, the surfaces of the first annular wall 151 and the second annular wall 152 of the double-layer sealing structure 150, which are matched with the labyrinth structure, are provided with an easily-abraded layer 154, and the easily-abraded layer 154 may be made of an elastic material, preferably, rubber, but not limited thereto. The abradable layer 154 is applied to the first and second annular walls 151, 152 of the inner wall panel 110 of the closure along a circumferential sub-area of the closure, preferably divided into four 90 ° semi-annular areas which are respectively applied to the first and second annular walls 151, 152 by gluing. In one embodiment, the abradable layer 154 has a thickness of 2.5-3 mm. When the abradable layer 154 is applied. The region of the abradable layer 154 is subjected to a pressure treatment. Preferably, the easily-abraded layer 154 can be pressurized by vacuum bag pressing, the vacuum pressure is pumped to-0.095 MPa, and the pressure is maintained for 1min to make the adhesion of the easily-abraded layer 154 more compact and reduce the porosity of the easily-abraded layer 154 area.
In another embodiment, the easily-wearable layer 154 is made of resin containing inorganic filler, preferably, the inorganic filler is talc or graphite, but not limited thereto. The inorganic filler is added into the resin, stirred and dispersed by an ultrasonic oscillator, and solidified to form an easily-abraded layer 154, and then the easily-abraded layer 154 is attached to the first annular wall 151 and the second annular wall 152 of the inner wall plate 110 of the sealing cover in different areas along the circumferential direction of the sealing cover, preferably, the easily-abraded layer is divided into four half-ring areas of 90 degrees and is respectively attached to the first annular wall 151 and the second annular wall 152 in an adhesive manner. In one embodiment, the abradable layer 154 has a thickness of 2.5-3 mm. When the abradable layer 154 is applied. The region of the abradable layer 154 is subjected to a pressure treatment. Preferably, the easily-abraded layer 154 can be pressurized by vacuum bag pressing, the vacuum pressure is pumped to-0.095 MPa, and the pressure is maintained for 1min to make the adhesion of the easily-abraded layer 154 more compact and reduce the porosity of the easily-abraded layer 154 area.
In one embodiment, the outer wall plate of the sealing cover is provided with a reinforcing rib structure, and the wall plate structure is matched with the sealing cover to increase the rigidity of the wall plate under the conditions that the thickness of the wall plate of the sealing cover is reduced and the structure is lightened. The cross-section of strengthening rib is one of "worker" or "L" type, adopts metal or combined material, sets up along the generating line direction of outer wallboard to along the equidistance symmetric distribution of sealed cowling circumference, can guarantee the homogeneity and the equilibrium of sealed cowling structure when reinforcing sealed cowling structure rigidity. Preferably, 4 reinforcing ribs which are distributed along the circumferential direction of the sealing cover at 90 degrees and are symmetrically distributed at equal intervals can be selected.
In one embodiment, the reinforcing rib material is a composite material, preferably, a carbon fiber composite material, but not limited thereto. The reinforcing rib is molded by adopting a pultrusion process, and the fibers of the composite material are distributed along the pultrusion direction of 0 degree, so that the maximum bending resistance efficiency of the reinforcing rib structure can be realized, and the continuous production can be realized. In another embodiment, the reinforcing bars are formed using an autoclave process.
In one embodiment, the unidirectional prepreg tape is adopted to fill the R-angle area of the reinforcing rib, so that the R-angle weak area of the reinforcing rib is strengthened, and the bending resistance of the reinforcing rib is better.
The density of the composite material sealing cover for the bearing cavity of the aeroengine manufactured by the method can meet the high-temperature and oil-resistant working environment of the sealing cover, and the weight of the engine is reduced. Meanwhile, the sealing cover manufactured by the method has smaller pores, and the strength and the quality can be ensured.
The above-mentioned embodiments are merely illustrative of the technical spirit and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the content of the present invention and to implement the same, so that the scope of the present invention should not be limited thereto, i.e., all equivalent changes and modifications made in the spirit of the present invention should be covered by the scope of the present invention.
Claims (28)
1. A method of making a composite material containment cap which cooperates with a labyrinth arrangement to form a seal arrangement, the containment cap comprising inner and outer wall panels between which a bleed air passage is formed by bleed air holes in the inner wall panel, the method comprising:
step a, impregnating a glass fiber cloth with bismaleimide resin to prepare a prepreg;
b, laying the prepreg by using a mould;
c, molding the laid prepreg to obtain the inner wall plate and the outer wall plate of the sealing cover;
step d, forming the air guide holes on the inner wall plate; wherein
The bleed air hole includes a first bleed air hole and a second bleed air hole formed on the inner wall panel.
2. The method of claim 1, wherein step b comprises laying up said prepreg on said inner wall panel mold and said outer wall panel mold, respectively;
the step c comprises respectively molding the prepreg on the mold of the inner wall plate and the prepreg on the mold of the outer wall plate to form the inner wall plate and the outer wall plate which are separated;
the method further comprises a step e of connecting the separated inner and outer wall panels.
3. The method of claim 2, wherein step c includes separately forming the inner and outer wall panels using autoclave or compression molding.
4. The method of claim 3 wherein said step c comprises separately forming said separated inner and outer wall panels by autoclave forming;
the method also comprises the step of pressurizing the laminated prepreg in the process of executing the step b.
5. The method of claim 1, wherein step b comprises laying up the prepreg on a thin-walled cavity mold common to the inner and outer wall panels;
and the step c comprises integrally molding the prepreg on the thin-wall cavity mold to form the integrated inner wall plate and outer wall plate.
6. The method of claim 5 wherein step c further comprises integrally forming said prepreg using autoclave or compression molding to form said integral inner and outer wall panels.
7. The method of claim 6, wherein the step c integrally forms the inner and outer wall panels by autoclave molding;
the method also comprises the step of pressurizing the laminated prepreg in the process of executing the step b.
8. The method of claim 1, wherein said step d includes machining said first gas port in said formed inner wall panel.
9. The method of claim 2, wherein said step d includes machining said second gas introduction hole in said formed inner wall panel.
10. The method of claim 5, wherein said step d includes cutting said prepreg at a desired location of said second vent during said step b, the cut area forming said second vent after said interior wall panel is formed.
11. The method of claim 1, wherein step b comprises applying a quasi-isotropic layup of the prepreg, the layup of the prepreg being carried out in circumferentially spaced apart regions of the mould;
connecting the prepregs in different areas on the uppermost layer and the lowermost layer of the paving layer in a splicing mode, wherein the width of a splicing seam part is 0-2 mm;
connecting the prepregs in different areas of each of the rest intermediate layers of the paving layer in an overlapping manner, wherein the width of the overlapping part is 0-2 mm;
the lap joint parts of the ply intermediate layers are staggered by 30 degrees uniformly along the circumferential direction of the seal cover between adjacent layers;
the splicing seam parts of the uppermost layer and the lowermost layer of the layer and the lap joint parts of the middle layer adjacent to the splicing seam parts are staggered by 30 degrees uniformly along the circumferential direction of the sealing cover.
12. The method of claim 11, wherein the quasi-isotropic layup employs one of (0 °/45 °/90 °)2s or (0 °/60 °)2 s.
13. The method of claim 1, further comprising forming an abradable layer on mating surfaces of the seal housing and the labyrinth structure;
the easily-abraded layer is made of one of elastic materials or resins containing inorganic fillers;
the easily-abraded layer is attached to the sealing cover in a partitioned mode along the circumferential direction of the sealing cover;
and carrying out pressurization treatment on the easily-abraded layer.
14. The method of claim 13, wherein the easily abradable layer is formed from an inorganic filler-containing resin;
the preparation method of the resin containing the inorganic filler comprises the following steps: adding an inorganic filler into resin, stirring and dispersing the inorganic filler by using an ultrasonic oscillator, and then curing to form the resin containing the inorganic filler;
the inorganic filler is one of talcum powder or graphite.
15. The method of claim 1, further comprising forming a bead on the seal can;
the section of the reinforcing rib is in one of I shape or L shape;
the reinforcing rib is made of one of metal or composite material;
and forming the reinforcing rib in a pultrusion mode.
16. The method of claim 15, wherein the ribs are disposed along a generatrix of the seal shroud and are equally spaced and symmetrically distributed along a circumference of the seal shroud.
17. The method of claim 15, wherein the reinforcing bar is a composite material, the composite material being a carbon fiber composite material;
the reinforcing rib is formed by pultrusion, and fibers of the carbon fiber composite material are distributed along the pultrusion direction of 0 degree.
18. The method of claim 15, wherein the reinforcing bars are of composite material and wherein the reinforcing bars are formed by autoclave.
19. The method of claim 15 wherein the R-corner regions of the ribs are filled with unidirectional prepreg tape.
20. A composite material containment cap for an aircraft engine bearing cavity formed according to the method of claim 1, the containment cap cooperating with a labyrinth structure to form a sealed structure, the containment cap comprising an inner wall panel and an outer wall panel, the inner wall panel and the outer wall panel defining a bleed air passage therebetween through first bleed air holes and second bleed air holes in the inner wall panel, the composite material being made from bismaleimide resin and fiberglass cloth.
21. The composite seal cap of claim 20, wherein said inner panel is of a neck-like flange configuration comprising an annular base plate, a reducing neck tube and a double seal configuration mating with said labyrinth configuration;
the first air guide holes are distributed on the circular ring base plate;
the pipe diameter of the reducing neck pipe gradually changes along the axial direction of the sealing cover, one end with the large pipe diameter is connected to the inner wall end of the circular ring chassis, and the other end with the small pipe diameter is connected to the double-layer sealing structure;
the double-layer sealing structure comprises two parallel annular walls along the radial direction of the sealing cover, the width of a first annular wall connected with the reducing neck pipe is larger than that of an adjacent second annular wall, one end of the first annular wall and one end of the second annular wall are positioned on the same horizontal plane in the axial direction of the sealing cover, the other end of the first annular wall is connected with the other end of the second annular wall through a thin-wall circular truncated cone, the grate structure acts on the inner wall surfaces of the first annular wall and the second annular wall, and second air guide holes are distributed on the wall surface of the first annular wall close to one end of the thin-wall circular truncated cone;
the outer wall plate and the inner wall plate are connected to the outer end wall of the circular ring chassis and the thin-wall circular truncated cone to form the air-entraining channel.
22. The composite seal cap of claim 21 wherein said first and second annular walls have an abradable layer on an inner wall surface in contact with said labyrinth structure;
the material of the easily-abraded layer is one of elastic material or resin containing inorganic filler.
23. The composite seal boot of claim 22, wherein said abradable layer is an elastomeric material, and wherein said elastomeric material is rubber.
24. The composite seal cap of claim 22, wherein said abradable layer is a resin containing a filler material, and wherein said inorganic filler is one of talc or graphite.
25. The composite seal cap of claim 21, wherein said seal cap has a rib structure, said rib having one of an "i" or "L" shaped cross-section, said rib being formed of one of a metal or a composite material.
26. The composite seal shroud of claim 25, wherein said ribs are disposed along a generatrix of said outer wall panel and are equally spaced and symmetrically disposed circumferentially along said shroud.
27. The composite seal boot of claim 25, wherein said reinforcing ribs are of composite material and said composite material is carbon fiber composite material.
28. The composite seal boot of claim 25, wherein said R-corner regions of said ribs are filled with unidirectional prepreg tape.
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