CN106747534A - A kind of aero-engine ceramic base diaphragm seal and preparation method thereof - Google Patents
A kind of aero-engine ceramic base diaphragm seal and preparation method thereof Download PDFInfo
- Publication number
- CN106747534A CN106747534A CN201611006734.6A CN201611006734A CN106747534A CN 106747534 A CN106747534 A CN 106747534A CN 201611006734 A CN201611006734 A CN 201611006734A CN 106747534 A CN106747534 A CN 106747534A
- Authority
- CN
- China
- Prior art keywords
- precast body
- diaphragm seal
- aero
- ceramic base
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- C04B35/806—
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
- C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
- C04B35/565—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide
- C04B35/571—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide obtained from Si-containing polymer precursors or organosilicon monomers
-
- D—TEXTILES; PAPER
- D04—BRAIDING; LACE-MAKING; KNITTING; TRIMMINGS; NON-WOVEN FABRICS
- D04C—BRAIDING OR MANUFACTURE OF LACE, INCLUDING BOBBIN-NET OR CARBONISED LACE; BRAIDING MACHINES; BRAID; LACE
- D04C1/00—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof
- D04C1/02—Braid or lace, e.g. pillow-lace; Processes for the manufacture thereof made from particular materials
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
- C04B2235/608—Green bodies or pre-forms with well-defined density
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/65—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes
- C04B2235/656—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes characterised by specific heating conditions during heat treatment
- C04B2235/6562—Heating rate
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/65—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes
- C04B2235/656—Aspects relating to heat treatments of ceramic bodies such as green ceramics or pre-sintered ceramics, e.g. burning, sintering or melting processes characterised by specific heating conditions during heat treatment
- C04B2235/6567—Treatment time
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
- C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
- C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
- C04B2235/9669—Resistance against chemicals, e.g. against molten glass or molten salts
- C04B2235/9684—Oxidation resistance
-
- D—TEXTILES; PAPER
- D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B2101/00—Inorganic fibres
- D10B2101/10—Inorganic fibres based on non-oxides other than metals
- D10B2101/14—Carbides; Nitrides; Silicides; Borides
- D10B2101/16—Silicon carbide
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Ceramic Engineering (AREA)
- Textile Engineering (AREA)
- Materials Engineering (AREA)
- Structural Engineering (AREA)
- Organic Chemistry (AREA)
- Ceramic Products (AREA)
Abstract
The present invention relates to technical field of aircraft engine part manufacture, specifically related to a kind of aero-engine ceramic base diaphragm seal and preparation method thereof, with silicon carbide fibre as raw material, the precast body of diaphragm seal is worked out using three-dimensional four step rule, 1.5 3h are heat-treated at 850 950 DEG C, carbon boundary layer is pyrolyzed in the surface deposition of precast body using chemical vapour deposition technique, using dipping, cracking technology treatment precast body, the density for the treatment of to precast body is not less than 1.9g/cm for circulating repetition3, silicon carbide substrate is obtained, silicon carbide substrate is machined, obtain aero-engine ceramic base diaphragm seal.Using prepared by ceramic matric composite forming, than virgin metal diaphragm seal loss of weight more than 40%, consistency reaches more than 90% to aero-engine ceramic base diaphragm seal of the invention, and bending strength reaches 721MPa, and inoxidizability improves 20%；Preparation method is simple simultaneously, and the obtained aero-engine ceramic base diaphragm seal life-span can reach more than 350 hours, meet aero-engine use requirement.
Description
Technical field
The present invention relates to technical field of aircraft engine part manufacture, and in particular to a kind of aero-engine ceramic base is close
Mounting and preparation method thereof.
Background technology
Aerial engine sealing piece is in high temperature, high pressure draught, while receiving hydraulic actuator retractable mechanical force and Nei Tong
Road air-flow Aerodynamic force action, therefore, the performance requirement to aerial engine sealing piece is very harsh.
China Patent Publication No. CN102921770A discloses a kind of K24 cast alloy materials diaphragm seal and adjustment sheet deformation
Repair process, is deformed using heat treatment method reparation is stablized；Specific stabilization Technology for Heating Processing code is as follows：It is warmed up to
1160 ± 10 DEG C, kept for 2-4 hours, 750 DEG C are cooled in stove；It is required that carrying out stablizing heat treatment under ar gas environment.The invention
Part deformation amount can be reduced more than 70%, but preparation technology is cast using high temperature alloy, is also easy to produce deformation, crackle, mistake
The failures such as heat, ablation, fracture, contact surface abrasion.
And on the other hand, ceramic matric composite has that proportion is small, specific strength big, high temperature resistant, wear-resistant, antioxygenic property
The features such as good.In space industry, ceramic matric composite extensive use, but less, existing skill is applied in aero-engine field
Ceramic matric composite is applied in aero-engine to significantly reduce engine weight in art, oil consumption is reduced.External M88 hairs
Motivation prepares diaphragm seal using carbon fibre reinforced silicon carbide matrix composite, in then being worked when long, but exposes antioxygen
The shortcomings of property changed is not enough.
Therefore, aero-engine is applied to solve the problems, such as above-mentioned ceramic matric composite, the present invention provides one kind and opens
Hair long-life ceramic matric composite diaphragm seal of high performance antioxidation and preparation method thereof, with make up it is of the prior art not
Foot, while meeting aero-engine use requirement.
The content of the invention
It is an object of the invention to overcome the deficiencies in the prior art, there is provided a kind of aero-engine ceramic base diaphragm seal and its
Preparation method, with ceramic matric composite as raw material, is worked out by three-dimensional four step rule, significantly improves obtained aviation hair
The consistency and bending strength of motivation ceramic base diaphragm seal, while loss of weight more than 40%, meets the use requirement of aero-engine.
The purpose of the present invention is achieved through the following technical solutions：
A kind of preparation method of aero-engine ceramic base diaphragm seal, comprises the following steps：
S1. with silicon carbide fibre as raw material, the precast body of diaphragm seal is worked out using three-dimensional four step rule；
S2. precast body is fitted into sealing die, 1.5-3h is heat-treated at 850-950 DEG C；
S3. the surface deposition using chemical vapour deposition technique in precast body is pyrolyzed carbon boundary layer；The chemical vapour deposition technique
Depositing temperature is 970-990 DEG C, and deposition pressure is 0.3-1.3kPa, and sedimentation time is 20-30h, meanwhile, using mass flow ratio
It is 10:1 natural gas and propane is precursor gas, and the pressure of natural gas and propane is 0.1MPa；
S4. using dipping, cracking technology treatment precast body, the density for the treatment of to precast body is not less than 1.9g/cm to circulating repetition3,
Obtain silicon carbide substrate；The impregnation technology is：By precast body in below vacuum pressure 50Pa, Polycarbosilane maceration extract is added,
Then 0.3-0.7MPa is forced into, 8-12h is impregnated, is dried；The cracking technology is：Precast body is placed in vacuum high temperature furnace,
550 DEG C are warming up to the programming rate of 200 DEG C/h, 0.5-1h is then incubated, then be warming up to the programming rate of 1100 DEG C/h
1100 DEG C, 1-1.5h is incubated, is cooled to room temperature；
S5. silicon carbide substrate is machined by fitted position requirement, obtains aero-engine ceramic base diaphragm seal.
Further, heat treatment is carried out in vacuum high temperature furnace in the step S2.
Further, circulating repetition is secondary using the circulating repetition of dipping, cracking technology treatment precast body in the step S4
Number is 12-15 times.
Further, when first three time circulating repetition is using dipping, cracking technology treatment precast body, use mass fraction for
20% Polycarbosilane；When last three circulating repetitions are using dipping, cracking technology treatment precast body, it is 50% to use mass fraction
Polycarbosilane；During remaining circulating repetition is using dipping, cracking technology treatment precast body, use mass fraction for 40% it is poly-
Carbon silane.
Further, in the impregnation technology, dry concrete operations to dry 0.5-2h naturally, then at 50-70 DEG C
Lower drying 8-12h.
Further, it is by the concrete operations that precast body loads sealing die in the step S2：Precast body is kept flat
In in lower template, then middle template and upper die plate are assembled and be positioned on precast body, will be pre- by alignment pin and stop collar
Body processed is positioned in a mold, is locked finally by nut, bolt, and the whole mould that precast body is will be equipped with after having assembled is put into high temperature
Vacuum drying oven.
A kind of aero-engine ceramic base diaphragm seal, is prepared from by the above method.
The beneficial effects of the invention are as follows：
1. aero-engine ceramic base diaphragm seal of the invention is sealed using prepared by ceramic matric composite forming than virgin metal
Piece loss of weight more than 40%；
2. preparation method of the invention uses the weaving manner of three-dimensional four step rule, and circulation dipping, cracking technology, significantly improves
Ceramic matric composite performance, makes consistency more than 90%, and bending strength reaches 721MPa；
3. compared to carbon fiber/carborundum diaphragm seal, inoxidizability is improved aero-engine ceramic base diaphragm seal of the invention
20%；
4. preparation method of the invention is simple, and the obtained aero-engine ceramic base diaphragm seal life-span can reach more than 350 hours,
Meet aero-engine use requirement.
Brief description of the drawings
Fig. 1 is the structure chart of present invention sealing die；
Fig. 2 is the sectional view of present invention sealing die；
Fig. 3 is the stereogram of present invention sealing die；
In figure, 1 is upper die plate, and 2 is middle template, and 3 is lower template, and 4 is alignment pin, and 5 is nut, and 6 is bolt, and 7 is stop collar, 8
It is precast body.
Specific embodiment
Technical scheme is described in further detail with reference to embodiment, but protection scope of the present invention is not limited to
In as described below.
Embodiment 1
A kind of preparation method of aero-engine ceramic base diaphragm seal, comprises the following steps：
S1. with silicon carbide fibre as raw material, the precast body of diaphragm seal is worked out using three-dimensional four step rule；
S2. precast body 8 is lain against in lower template 3, then middle template 2 and upper die plate 1 is assembled and be positioned over precast body 8
On, precast body 8 is positioned in a mold by alignment pin 4 and stop collar 7, locked finally by nut 5, bolt 6.After having assembled
The whole mould that will be equipped with precast body 8 is put into vacuum high temperature furnace, and 3h is heat-treated at 850 DEG C；
S3. the surface deposition using chemical vapour deposition technique in precast body is pyrolyzed carbon boundary layer；The chemical vapour deposition technique
Depositing temperature is 970 DEG C, and deposition pressure is 1.3kPa, and sedimentation time is 25h, meanwhile, it is 10 to use mass flow ratio:1 day
Right gas and propane are precursor gas, and the pressure of natural gas and propane is 0.1MPa；
S4. using dipping, cracking technology treatment precast body, circulating repetition number of times is 12 times to circulating repetition, treatment to precast body
Density is not less than 1.9g/cm3, obtain silicon carbide substrate；
The impregnation technology is：By precast body in below vacuum pressure 50Pa, Polycarbosilane maceration extract is added, be then forced into
0.3MPa, impregnates 12h, and 2h is dried naturally, then dries 12h at 50 DEG C；
The cracking technology is：Precast body is placed in vacuum high temperature furnace, 550 DEG C is warming up to the programming rate of 200 DEG C/h, so
After be incubated 1h, then be warming up to 1100 DEG C with the programming rate of 1100 DEG C/h, be incubated 1h, be cooled to room temperature；
When first three time circulating repetition is using dipping, cracking technology treatment precast body, use mass fraction for 20% Polycarbosilane；
When last three circulating repetitions are using dipping, cracking technology treatment precast body, use mass fraction for 50% Polycarbosilane；It is remaining
Under circulating repetition using dipping, cracking technology treatment precast body in, use mass fraction for 40% Polycarbosilane.
S5. silicon carbide substrate is machined by fitted position requirement, obtains aero-engine ceramic base diaphragm seal.
Embodiment 2
A kind of preparation method of aero-engine ceramic base diaphragm seal, comprises the following steps：
S1. with silicon carbide fibre as raw material, the precast body of diaphragm seal is worked out using three-dimensional four step rule；
S2. precast body 8 is lain against in lower template 3, then middle template 2 and upper die plate 1 is assembled and be positioned over precast body 8
On, precast body 8 is positioned in a mold by alignment pin 4 and stop collar 7, locked finally by nut 5, bolt 6.After having assembled
The whole mould that will be equipped with precast body 8 is put into vacuum high temperature furnace, and 1.5h is heat-treated at 950 DEG C；
S3. the surface deposition using chemical vapour deposition technique in precast body is pyrolyzed carbon boundary layer；The chemical vapour deposition technique
Depositing temperature is 990 DEG C, and deposition pressure is 0.3kPa, and sedimentation time is 30h, meanwhile, it is 10 to use mass flow ratio:1 day
Right gas and propane are precursor gas, and the pressure of natural gas and propane is 0.1MPa；
S4. using dipping, cracking technology treatment precast body, circulating repetition number of times is 15 times to circulating repetition, treatment to precast body
Density is not less than 1.9g/cm3, obtain silicon carbide substrate；
The impregnation technology is：By precast body in below vacuum pressure 50Pa, Polycarbosilane maceration extract is added, be then forced into
0.7MPa, impregnates 8h, and 0.5h is dried naturally, then dries 8h at 70 DEG C；
The cracking technology is：Precast body is placed in vacuum high temperature furnace, 550 DEG C is warming up to the programming rate of 200 DEG C/h, so
After be incubated 0.5h, then be warming up to 1100 DEG C with the programming rate of 1100 DEG C/h, be incubated 1.5h, be cooled to room temperature；
When first three time circulating repetition is using dipping, cracking technology treatment precast body, use mass fraction for 20% Polycarbosilane；
When last three circulating repetitions are using dipping, cracking technology treatment precast body, use mass fraction for 50% Polycarbosilane；It is remaining
Under circulating repetition using dipping, cracking technology treatment precast body in, use mass fraction for 40% Polycarbosilane.
S5. silicon carbide substrate is machined by fitted position requirement, obtains aero-engine ceramic base diaphragm seal.
Embodiment 3
A kind of preparation method of aero-engine ceramic base diaphragm seal, comprises the following steps：
S1. with silicon carbide fibre as raw material, the precast body of diaphragm seal is worked out using three-dimensional four step rule；
S2. precast body 8 is lain against in lower template 3, then middle template 2 and upper die plate 1 is assembled and be positioned over precast body 8
On, precast body 8 is positioned in a mold by alignment pin 4 and stop collar 7, locked finally by nut 5, bolt 6.After having assembled
The whole mould that will be equipped with precast body 8 is put into vacuum high temperature furnace, and 2h is heat-treated at 900 DEG C；
S3. the surface deposition using chemical vapour deposition technique in precast body is pyrolyzed carbon boundary layer；The chemical vapour deposition technique
Depositing temperature is 980 DEG C, and deposition pressure is 0.8kPa, and sedimentation time is 25h, meanwhile, it is 10 to use mass flow ratio:1 day
Right gas and propane are precursor gas, and the pressure of natural gas and propane is 0.1MPa；
S4. using dipping, cracking technology treatment precast body, circulating repetition number of times is 14 times to circulating repetition, treatment to precast body
Density is not less than 1.9g/cm3, obtain silicon carbide substrate；
The impregnation technology is：By precast body in below vacuum pressure 50Pa, Polycarbosilane maceration extract is added, be then forced into
0.5MPa, impregnates 10h, and 1h is dried naturally, then dries 10h at 60 DEG C；
The cracking technology is：Precast body is placed in vacuum high temperature furnace, 550 DEG C is warming up to the programming rate of 200 DEG C/h, so
After be incubated 0.6h, then be warming up to 1100 DEG C with the programming rate of 1100 DEG C/h, be incubated 1.2h, be cooled to room temperature；
When first three time circulating repetition is using dipping, cracking technology treatment precast body, use mass fraction for 20% Polycarbosilane；
When last three circulating repetitions are using dipping, cracking technology treatment precast body, use mass fraction for 50% Polycarbosilane；It is remaining
Under circulating repetition using dipping, cracking technology treatment precast body in, use mass fraction for 40% Polycarbosilane.
S5. silicon carbide substrate is machined by fitted position requirement, obtains aero-engine ceramic base diaphragm seal.
Embodiment 4
A kind of preparation method of aero-engine ceramic base diaphragm seal, comprises the following steps：
S1. with silicon carbide fibre as raw material, the precast body of diaphragm seal is worked out using three-dimensional four step rule；
S2. precast body 8 is lain against in lower template 3, then middle template 2 and upper die plate 1 is assembled and be positioned over precast body 8
On, precast body 8 is positioned in a mold by alignment pin 4 and stop collar 7, locked finally by nut 5, bolt 6.After having assembled
The whole mould that will be equipped with precast body 8 is put into vacuum high temperature furnace, and 2h is heat-treated at 900 DEG C；
S3. the surface deposition using chemical vapour deposition technique in precast body is pyrolyzed carbon boundary layer；The chemical vapour deposition technique
Depositing temperature is 980 DEG C, and deposition pressure is 1kPa, and sedimentation time is 25h, meanwhile, it is 10 to use mass flow ratio:1 it is natural
Gas and propane are precursor gas, and the pressure of natural gas and propane is 0.1MPa；
S4. using dipping, cracking technology treatment precast body, circulating repetition number of times is 14 times to circulating repetition, treatment to precast body
Density is not less than 1.9g/cm3, obtain silicon carbide substrate；
The impregnation technology is：By precast body in below vacuum pressure 50Pa, Polycarbosilane maceration extract is added, be then forced into
0.6MPa, impregnates 10h, and 1h is dried naturally, then dries 10h at 65 DEG C；
The cracking technology is：Precast body is placed in vacuum high temperature furnace, 550 DEG C is warming up to the programming rate of 200 DEG C/h, so
After be incubated 0.8h, then be warming up to 1100 DEG C with the programming rate of 1100 DEG C/h, be incubated 1h, be cooled to room temperature；
When first three time circulating repetition is using dipping, cracking technology treatment precast body, use mass fraction for 20% Polycarbosilane；
When last three circulating repetitions are using dipping, cracking technology treatment precast body, use mass fraction for 50% Polycarbosilane；It is remaining
Under circulating repetition using dipping, cracking technology treatment precast body in, use mass fraction for 40% Polycarbosilane.
S5. silicon carbide substrate is machined by fitted position requirement, obtains aero-engine ceramic base diaphragm seal.
The above is only the preferred embodiment of the present invention, it should be understood that the present invention is not limited to described herein
Form, is not to be taken as the exclusion to other embodiment, and can be used for various other combinations, modification and environment, and can be at this
In the text contemplated scope, it is modified by the technology or knowledge of above-mentioned teaching or association area.And those skilled in the art are entered
Capable change and change does not depart from the spirit and scope of the present invention, then all should be in the protection domain of appended claims of the present invention
It is interior.
Claims (7)
1. a kind of preparation method of aero-engine ceramic base diaphragm seal, it is characterised in that comprise the following steps：
S1. with silicon carbide fibre as raw material, the precast body of diaphragm seal is worked out using three-dimensional four step rule；
S2. precast body is fitted into sealing die, 1.5-3h is heat-treated at 850-950 DEG C；
S3. the surface deposition using chemical vapour deposition technique in precast body is pyrolyzed carbon boundary layer；The chemical vapour deposition technique
Depositing temperature is 970-990 DEG C, and deposition pressure is 0.3-1.3kPa, and sedimentation time is 20-30h, meanwhile, using mass flow ratio
It is 10:1 natural gas and propane is precursor gas, and the pressure of natural gas and propane is 0.1MPa；
S4. using dipping, cracking technology treatment precast body, the density for the treatment of to precast body is not less than 1.9g/cm to circulating repetition3, obtain
To silicon carbide substrate；The impregnation technology is：By precast body in below vacuum pressure 50Pa, Polycarbosilane maceration extract is added, so
After be forced into 0.3-0.7MPa, impregnate 8-12h, dry；The cracking technology is：Precast body is placed in vacuum high temperature furnace, with
The programming rate of 200 DEG C/h is warming up to 550 DEG C, is then incubated 0.5-1h, then be warming up to 1100 with the programming rate of 1100 DEG C/h
DEG C, 1-1.5h is incubated, it is cooled to room temperature；
S5. silicon carbide substrate is machined, obtains aero-engine ceramic base diaphragm seal.
2. the preparation method of a kind of aero-engine ceramic base diaphragm seal according to claim 1, it is characterised in that described
Heat treatment is carried out in vacuum high temperature furnace in step S2.
3. the preparation method of a kind of aero-engine ceramic base diaphragm seal according to claim 1, it is characterised in that described
Circulating repetition uses dipping, the circulating repetition number of times of cracking technology treatment precast body for 12-15 times in step S4.
4. the preparation method of a kind of aero-engine ceramic base diaphragm seal according to claim 3, it is characterised in that：First three
When secondary circulating repetition is using dipping, cracking technology treatment precast body, use mass fraction for 20% Polycarbosilane；Last three times
Circulating repetition using dipping, cracking technology treatment precast body when, use mass fraction for 50% Polycarbosilane；Remaining circulation
Repeat using dipping, cracking technology treatment precast body in, use mass fraction for 40% Polycarbosilane.
5. the preparation method of a kind of aero-engine ceramic base diaphragm seal according to claim 1, it is characterised in that described
In impregnation technology, then dry concrete operations dry 8-12h to dry 0.5-2h naturally at 50-70 DEG C.
6. the preparation method of a kind of aero-engine ceramic base diaphragm seal according to claim 1, it is characterised in that described
It is by the concrete operations that precast body loads sealing die in step S2：Precast body is lain against in lower template, then by middle mould
Plate is assembled and is positioned on precast body with upper die plate, is positioned precast body in a mold by alignment pin and stop collar, finally
Locked by nut, bolt, the whole mould that precast body is will be equipped with after having assembled is put into vacuum high temperature furnace.
7. a kind of aero-engine ceramic base diaphragm seal, it is characterised in that prepared by claim 1-6 any one methods described
Form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611006734.6A CN106747534A (en) | 2016-11-16 | 2016-11-16 | A kind of aero-engine ceramic base diaphragm seal and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611006734.6A CN106747534A (en) | 2016-11-16 | 2016-11-16 | A kind of aero-engine ceramic base diaphragm seal and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106747534A true CN106747534A (en) | 2017-05-31 |
Family
ID=58968830
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611006734.6A Pending CN106747534A (en) | 2016-11-16 | 2016-11-16 | A kind of aero-engine ceramic base diaphragm seal and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106747534A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107266099A (en) * | 2017-06-16 | 2017-10-20 | 中国人民解放军第五七九工厂 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
| CN109180194A (en) * | 2018-09-28 | 2019-01-11 | 中国人民解放军第五七九工厂 | A kind of compound density method of the different conditions polymer infiltration and pyrolysis of SiC based composites |
| CN109485427A (en) * | 2018-10-26 | 2019-03-19 | 中国人民解放军第五七九工厂 | A kind of PIP method for rapidly densifying of SiCf/SiC composite preform |
| CN111517796A (en) * | 2020-04-18 | 2020-08-11 | 西北工业大学 | Ceramic matrix composite elastic sealing element for aero-engine and preparation method thereof |
| CN114044688A (en) * | 2021-11-22 | 2022-02-15 | 北京航空航天大学 | Densification tool mold and densification method for ceramic matrix composite substrate |
| CN114800797A (en) * | 2022-05-19 | 2022-07-29 | 西北工业大学 | Multipurpose mold and application thereof |
| CN115838294A (en) * | 2022-12-27 | 2023-03-24 | 西安鑫垚陶瓷复合材料股份有限公司 | Preparation method of ceramic matrix composite material adjusting sheet or sealing sheet and shaping mold |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101503305A (en) * | 2009-02-03 | 2009-08-12 | 西北工业大学 | Process for preparing self-sealing silicon carbide ceramic based composite material |
| CN101913894A (en) * | 2010-07-08 | 2010-12-15 | 西北工业大学 | Dual self-healing modification method for silicon carbide ceramic matrix composite material |
| CN102910927A (en) * | 2012-11-16 | 2013-02-06 | 中国航空工业集团公司北京航空制造工程研究所 | Method for preparing self-healing silicon carbide ceramic-based composite material |
-
2016
- 2016-11-16 CN CN201611006734.6A patent/CN106747534A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101503305A (en) * | 2009-02-03 | 2009-08-12 | 西北工业大学 | Process for preparing self-sealing silicon carbide ceramic based composite material |
| CN101913894A (en) * | 2010-07-08 | 2010-12-15 | 西北工业大学 | Dual self-healing modification method for silicon carbide ceramic matrix composite material |
| CN102910927A (en) * | 2012-11-16 | 2013-02-06 | 中国航空工业集团公司北京航空制造工程研究所 | Method for preparing self-healing silicon carbide ceramic-based composite material |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107266099A (en) * | 2017-06-16 | 2017-10-20 | 中国人民解放军第五七九工厂 | A kind of aero-engine ceramic matrix composite turbine stator blade near-net-shape fixture |
| CN109180194A (en) * | 2018-09-28 | 2019-01-11 | 中国人民解放军第五七九工厂 | A kind of compound density method of the different conditions polymer infiltration and pyrolysis of SiC based composites |
| CN109180194B (en) * | 2018-09-28 | 2021-10-19 | 中国人民解放军第五七一九工厂 | Composite densification method for impregnation cracking of precursors in different states of SiC-based composite material |
| CN109485427A (en) * | 2018-10-26 | 2019-03-19 | 中国人民解放军第五七九工厂 | A kind of PIP method for rapidly densifying of SiCf/SiC composite preform |
| CN111517796A (en) * | 2020-04-18 | 2020-08-11 | 西北工业大学 | Ceramic matrix composite elastic sealing element for aero-engine and preparation method thereof |
| CN114044688A (en) * | 2021-11-22 | 2022-02-15 | 北京航空航天大学 | Densification tool mold and densification method for ceramic matrix composite substrate |
| CN114800797A (en) * | 2022-05-19 | 2022-07-29 | 西北工业大学 | Multipurpose mold and application thereof |
| CN115838294A (en) * | 2022-12-27 | 2023-03-24 | 西安鑫垚陶瓷复合材料股份有限公司 | Preparation method of ceramic matrix composite material adjusting sheet or sealing sheet and shaping mold |
| CN115838294B (en) * | 2022-12-27 | 2024-01-23 | 西安鑫垚陶瓷复合材料股份有限公司 | Preparation method of ceramic matrix composite regulating sheet or sealing sheet and shaping die |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106747534A (en) | A kind of aero-engine ceramic base diaphragm seal and preparation method thereof | |
| CN106977217B (en) | A kind of preparation method of high-strength and high-ductility silicon carbide fiber reinforced silicon carbide ceramic matric composite | |
| CN106699209B (en) | The preparation method of continuous alumina fiber enhancing alumina ceramic-base composites | |
| CN106927846B (en) | A kind of preparation method of C/C-SiC composite material parts and products thereof | |
| CN105060913B (en) | A kind of preparation method of low thermal coefficient of expansion C/C SiC ceramic matrix composite materials | |
| US9404185B2 (en) | Process for smoothing the surface of a part made of CMC material | |
| CN102910927B (en) | Method for preparing self-healing silicon carbide ceramic-based composite material | |
| CN106957180A (en) | A kind of Cf/ C SiC ceramic matrix composite materials and its preparation method and application | |
| CN106542837B (en) | Method for synthesizing SiC nanowire toughened multilayer structure SiC-C/C composite material | |
| CN111018537A (en) | Method for preparing carbon fiber reinforced SiC ceramic matrix composite material through 3D printing | |
| CN107353025A (en) | A kind of preparation method of resistance to 1200 DEG C of oxidation resistant ceramic matric composites | |
| CN106966747B (en) | One kind prepares aero-engine composite turbine blisks and preparation method and application | |
| CN103979974B (en) | A kind of C/SiC-HfB 2the preparation method of-HfC ultra-temperature ceramic-based composite material | |
| CN104072183B (en) | A kind of method of fibre reinforced stratiform woodceramics | |
| CN106565262A (en) | Preparation method for low-density refractory and antioxidative carbon-ceramic composite material | |
| CN102173844A (en) | Carbon fiber reinforced boron nitride composite and preparation method thereof | |
| CN108249944A (en) | SiO (silicon dioxide)2Process for preparing base composite material | |
| CN105272256B (en) | A kind of high heat conduction graphite foam/carbon composite and preparation method thereof | |
| CN111070726A (en) | Integral forming method of fiber reinforced SiC-based composite material reinforced thermal bearing structure | |
| CN104529499B (en) | A kind of preparation method of self-sealing silicon carbide fiber reinforcement silicon boron nitrogen carbon composite | |
| CN107082651A (en) | A kind of coat of silicon carbide and preparation method thereof | |
| CN106747531B (en) | A kind of polynary carbon and ceramic base thermostructural composite and its turbo blade without surplus preparation method | |
| CN105016760A (en) | Preparation method for ultra-high-temperature ceramic modified C/C composite material | |
| CN107226707A (en) | A kind of preparation method of SiC/Si B C Zr ceramic matric composites | |
| CN106977218B (en) | A kind of polynary carbon and ceramic matric composite piston and preparation method and application |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170531 |
|
| RJ01 | Rejection of invention patent application after publication |