CN113929467B - Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap - Google Patents
Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap Download PDFInfo
- Publication number
- CN113929467B CN113929467B CN202111199678.3A CN202111199678A CN113929467B CN 113929467 B CN113929467 B CN 113929467B CN 202111199678 A CN202111199678 A CN 202111199678A CN 113929467 B CN113929467 B CN 113929467B
- Authority
- CN
- China
- Prior art keywords
- sic
- blade body
- gap
- flow
- ceramic composite
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000919 ceramic Substances 0.000 title claims abstract description 27
- 239000002131 composite material Substances 0.000 title claims abstract description 27
- 238000001816 cooling Methods 0.000 title claims abstract description 24
- 238000002360 preparation method Methods 0.000 title claims abstract description 22
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims abstract description 120
- 229910010271 silicon carbide Inorganic materials 0.000 claims abstract description 120
- 238000007493 shaping process Methods 0.000 claims abstract description 27
- 238000000034 method Methods 0.000 claims abstract description 26
- 238000012545 processing Methods 0.000 claims abstract description 21
- 239000004744 fabric Substances 0.000 claims abstract description 20
- 238000000151 deposition Methods 0.000 claims abstract description 18
- 230000008021 deposition Effects 0.000 claims abstract description 8
- 239000011159 matrix material Substances 0.000 claims abstract description 6
- 238000004519 manufacturing process Methods 0.000 claims abstract description 4
- 238000004804 winding Methods 0.000 claims abstract description 4
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 18
- 238000007865 diluting Methods 0.000 claims description 13
- 239000000758 substrate Substances 0.000 claims description 13
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 12
- 238000009958 sewing Methods 0.000 claims description 11
- 229910052582 BN Inorganic materials 0.000 claims description 9
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims description 9
- 229910052786 argon Inorganic materials 0.000 claims description 9
- 238000005229 chemical vapour deposition Methods 0.000 claims description 9
- 230000005587 bubbling Effects 0.000 claims description 6
- 239000000835 fiber Substances 0.000 claims description 6
- 239000007789 gas Substances 0.000 claims description 6
- 239000005055 methyl trichlorosilane Substances 0.000 claims description 6
- JLUFWMXJHAVVNN-UHFFFAOYSA-N methyltrichlorosilane Chemical compound C[Si](Cl)(Cl)Cl JLUFWMXJHAVVNN-UHFFFAOYSA-N 0.000 claims description 6
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 claims description 5
- 238000011065 in-situ storage Methods 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 238000004140 cleaning Methods 0.000 claims description 4
- 229910002804 graphite Inorganic materials 0.000 claims description 4
- 239000010439 graphite Substances 0.000 claims description 4
- 239000001257 hydrogen Substances 0.000 claims description 4
- 229910052739 hydrogen Inorganic materials 0.000 claims description 4
- 238000010030 laminating Methods 0.000 claims description 4
- 238000013178 mathematical model Methods 0.000 claims description 3
- 238000003801 milling Methods 0.000 claims description 3
- 239000002994 raw material Substances 0.000 claims description 3
- FAQYAMRNWDIXMY-UHFFFAOYSA-N trichloroborane Chemical compound ClB(Cl)Cl FAQYAMRNWDIXMY-UHFFFAOYSA-N 0.000 claims description 3
- 229910021529 ammonia Inorganic materials 0.000 claims description 2
- 238000009423 ventilation Methods 0.000 abstract description 3
- 150000002431 hydrogen Chemical class 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011153 ceramic matrix composite Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000007669 thermal treatment Methods 0.000 description 1
Images
Classifications
-
- 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
-
- 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
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
-
- 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
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic 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
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/38—Non-oxide ceramic constituents or additives
- C04B2235/3852—Nitrides, e.g. oxynitrides, carbonitrides, oxycarbonitrides, lithium nitride, magnesium nitride
- C04B2235/386—Boron nitrides
-
- 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
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
-
- 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
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5252—Fibers having a specific pre-form
- C04B2235/5256—Two-dimensional, e.g. woven structures
-
- 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
- C04B2235/614—Gas infiltration of green bodies or pre-forms
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Organic Chemistry (AREA)
- Structural Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Inorganic Chemistry (AREA)
- Composite Materials (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Ceramic Products (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a preparation method of a SiC/SiC ceramic composite blade body component, in particular to a preparation method of a SiC/SiC ceramic composite blade body component with a tiny turbulence column cooling gap, and aims to solve the technical problems that the existing SiC/SiC ceramic composite blade body component has high processing difficulty of an air outlet hole and is difficult to realize ventilation and cooling of the blade body component by adjusting the size of the air outlet hole. The method comprises the steps of winding SiC/SiC two-dimensional plain cloth on a blade body inner mold shaping mold, prefabricating a gap with the width of 0.7mm at the air outlet hole end at the rear end of a blade body, processing the gap through interface layer deposition, high-temperature treatment and silicon carbide matrix layer deposition to obtain a blade body part meeting the corresponding required specification after reaching a certain density, riveting a silicon carbide pin at the rear end of the blade body according to a certain size on the premise of ensuring the reserved gap of the blade body, then depositing the silicon carbide matrix layer, enabling the blade body component to finally meet the required density and performance requirements, and manufacturing the blade body component meeting the designed and used requirements.
Description
Technical Field
The invention relates to a preparation method of a SiC/SiC ceramic composite blade body component, in particular to a preparation method of a SiC/SiC ceramic composite blade body component with a micro turbulence column cooling gap.
Background
The SiC/SiC ceramic composite material blade body component belongs to a high-temperature thermal structure component of a typical aeroengine, and needs to have excellent heat resistance and better bearing capacity, and along with the continuous development of engine technology, the engine provides more severe requirements on the structural strength, rigidity and fatigue resistance of the blade body component, so that a technological method for further exploring the higher temperature resistance of the SiC/SiC ceramic composite material is needed. However, the processing difficulty of the air outlet holes of the existing blade body components is high, and the ventilation and cooling of the blade body components are difficult to realize by adjusting the sizes of the air outlet holes.
Disclosure of Invention
The invention aims to solve the technical problems that the existing SiC/SiC ceramic composite blade body component has high processing difficulty of air outlet holes and is difficult to realize ventilation and cooling of the blade body component by adjusting the size of the air outlet holes, and provides a preparation method of the SiC/SiC ceramic composite blade body component with a tiny turbulence column cooling gap.
In order to solve the technical problems, the technical solution provided by the invention is as follows:
a preparation method of a SiC/SiC ceramic composite blade body component with a small turbulence column cooling gap is characterized by comprising the following steps:
1) Raw material selection and processing of inner and outer die shaping die of blade body
A) Selecting high-strength graphite, and processing and manufacturing an inner and outer die shaping die of the blade body;
b) Selecting SiC/SiC two-dimensional plain cloth;
2) Shaping
Shaping and sewing a prefabricated part meeting the process requirements by utilizing a shaping die of an inner die and an outer die of the blade body and adopting a two-dimensional laminating and in-situ sewing method, and reserving a gap at the vent hole of the prefabricated part;
3) Preparation of boron nitride interface layer
Placing the prefabricated body into a chemical vapor deposition furnace, and depositing a boron nitride interface layer with a certain thickness on the fiber surface of the prefabricated body according to preset temperature, pressure, flow and time;
4) Preparation of silicon carbide substrate layer
Depositing a silicon carbide substrate layer with a certain thickness on the surface of the preform on which the boron nitride interface layer is deposited in a chemical vapor deposition furnace according to preset temperature, pressure, flow and time;
5) Numerical milling machine
Processing the profile size of the blade body of the prefabricated body deposited with the silicon carbide substrate layer according to a preset processing mathematical model and a numerical control processing program;
6) Turbulent flow column processing
Cleaning the reserved gap, processing a turbulence column hole at the rear edge of the prefabricated blade body, and riveting a SiC/SiC pin at the turbulence column hole to serve as a turbulence column;
7) Silicon carbide substrate deposition
And putting the riveted prefabricated body into a chemical vapor deposition furnace again, and depositing a silicon carbide substrate layer meeting certain density requirements on the surface of the prefabricated body according to preset temperature, pressure, flow and time to obtain the SiC/SiC ceramic composite blade body member with the micro turbulence column cooling gap.
Further, in step 2), the preform meeting the process requirements is shaped and sewn by using the shaping die of the inner die and the outer die of the blade body and adopting a two-dimensional lamination and in-situ sewing method, and the method specifically includes the following steps:
2.1 Winding SiC/SiC two-dimensional plain cloth on the blade body inner mold shaping mold;
2.2 Sewing the wound SiC/SiC two-dimensional plain cloth by using the silicon carbide fiber so that the SiC/SiC two-dimensional plain cloth is tightly attached to the inner mold shaping mold of the blade body;
2.3 The sewn SiC/SiC two-dimensional plain cloth is fixed by using an outer mold, and a preform satisfying a predetermined thickness is obtained by using a gap between the inner and outer molds.
Further, in step 3), the preset temperature, pressure, flow rate and time are specifically:
the temperature is 200-1000 ℃, the pressure is less than 1500Pa, and the time is 24-100 h;
the flow rate is as follows: the flow rate of diluted argon is 0.2-1.5L/min, the flow rate of diluted hydrogen is 0.2-1.5L/min, the flow rate of ammonia is 0.05-0.8L/min, and the flow rate of boron trichloride is 0.01-0.8L/min.
Further, in step 4), the preset temperature, pressure, flow rate and time are specifically:
the temperature is 500-1500 ℃, the pressure is less than 3500Pa, and the time is 24-180 h;
the flow rate is as follows: bubbling hydrogen gas 1-10L/min, diluting hydrogen gas 0.1-10L/min, diluting argon gas 0.1-10L/min and methyl trichlorosilane 5-70L/min.
Further, in step 7), the preset temperature, pressure, flow rate and time are specifically:
the temperature is 500-1500 ℃, the pressure is less than 3500Pa, and the time is 24-180 h;
the flow rate is as follows: bubbling hydrogen gas 1-10L/min, diluting hydrogen gas 0.1-10L/min, diluting argon gas 0.1-10L/min and methyl trichlorosilane 5-70L/min.
Further, cleaning the reserved gap in the step 6) until the reserved gap is flat and free of concave-convex points.
Further, in the step 2), the width of the gap is 0.7mm.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention provides a preparation method of a SiC/SiC ceramic composite blade body component with a small turbulence column cooling gap, which is characterized in that SiC/SiC two-dimensional plain cloth is wound on a blade body inner mold shaping mold, a gap with the width of 0.7mm is prefabricated at the air outlet end at the rear end of a blade body, and is subjected to interface layer deposition, high-temperature treatment and silicon carbide matrix layer deposition to form a blade body part meeting the corresponding requirement specification after reaching a certain density, then a silicon carbide pin (namely a turbulence column) is riveted at the rear end of the blade body according to a certain size on the premise of ensuring the gap reserved on the blade body, and then the silicon carbide matrix layer deposition is carried out, so that the blade body component finally meets the density and performance requirements, and the blade body component (part) meeting the design and use requirements is manufactured. According to the method, the turbulence columns are creatively added in the gaps (cleft seams) of the blade body parts, the contact area of the cold air in the blade body is increased, the retention time of the cold air is prolonged, the air permeability and cooling performance of the blade body parts made of the ceramic matrix composite material are greatly improved, the problem of high difficulty in processing the air outlet holes of the blade body parts is effectively solved, and the method has very important significance and positive effect on improving the heat resistance of the blade body parts made of the SiC/SiC ceramic composite material.
2. The preparation method of the SiC/SiC ceramic composite blade body component with the small turbulence column cooling gap provided by the invention has the advantages of stable process and controllable quality; the manufacturability is strong, and the requirement on the preformed body reserved gap is not high; the process has good adaptability and can meet the production requirements of blade parts of various specifications.
Drawings
FIG. 1 is a flow chart of the preparation of a preform with a predetermined thickness of a SiC/SiC ceramic composite blade member with a small spoiler column cooling gap according to the present invention, wherein A is a blade inner mold shaping mold, B is SiC/SiC two-dimensional plain cloth, C1 is a lower half portion of an outer mold, and C2 is an upper half portion of the outer mold;
FIG. 2 is a schematic structural view of the SiC/SiC ceramic composite blade member with the micro spoiler column cooling gap according to the present invention;
FIG. 3 is a side view of a SiC/SiC ceramic composite airfoil member with a micro turbulator post cooling gap in accordance with the present invention;
FIG. 4 is an enlarged view of a portion of the spoiler in FIG. 3;
description of reference numerals:
1-blade body member, 2-gap and 3-turbulence column.
Detailed Description
The invention is further described below with reference to the figures and examples.
A preparation method of a SiC/SiC ceramic composite blade body component with a small turbulence column cooling gap comprises the following steps:
1) Raw material selection and processing of inner and outer blade mould shaping mould
A) Selecting high-strength graphite (the volume density is more than or equal to 1.75 g/cm) 3 Resistivity is less than or equal to 8USLm, flexural strength is more than or equal to 13MPa, compressive strength is more than or equal to 30MPa, and thermal expansion coefficient isThe number is less than or equal to 2.5, the gray level is less than or equal to 0.3 percent, and an inner and outer die shaping die (a graphite inner die) of the blade body is processed and manufactured;
b) Selecting SiC/SiC two-dimensional plain cloth (silicon carbide cloth);
2) Shaping
Shaping and sewing a prefabricated part meeting the process requirements by utilizing a shaping die of an inner die and an outer die of a blade body and adopting a two-dimensional laminating and in-situ sewing method, and reserving a gap with the width of 0.7mm at a vent hole of the prefabricated part, wherein the process requirements specifically refer to the following steps:
as shown in fig. 1, the specific method is as follows:
2.1 Winding SiC/SiC two-dimensional plain cloth on the blade body inner mold shaping mold;
2.2 Sewing the wound SiC/SiC two-dimensional plain cloth by using the silicon carbide fiber to ensure that the SiC/SiC two-dimensional plain cloth is tightly attached to the inner mold shaping mold of the blade body;
2.3 Fixing the sewed SiC/SiC two-dimensional plain cloth by using an outer mold, and obtaining a prefabricated body meeting the preset thickness (namely controlling the thickness of a silicon carbide cloth layer) by using a gap between the inner mold and the outer mold;
the outer mold can be prepared by the conventional technical means in the field, and only a prefabricated part meeting the preset thickness can be obtained after the outer mold is matched with the blade inner mold shaping mold for use;
3) Preparation of boron nitride interface layer
Putting the prefabricated body into a chemical vapor deposition furnace, and performing thermal treatment according to the preset temperature of 450 ℃, the pressure of less than 1200Pa, the time of 48h and the flow: diluting argon gas for 0.9L/min, diluting hydrogen gas for 0.9L/min, ammonia gas for 0.75L/min and boron trichloride for 0.7L/min, and depositing a boron nitride interface layer with a certain thickness on the surface of the prefabricated fiber;
4) Preparation of silicon carbide substrate layer
Placing the preform with the deposited boron nitride interface layer in a chemical vapor deposition furnace, and performing reaction according to the preset temperature of 800 ℃, pressure of 2300Pa, time of 120h, flow: 8L/min of bubbling hydrogen, 8L/min of diluting hydrogen, 6.8L/min of diluting argon and 25L/min of methyltrichlorosilane, and depositing a silicon carbide substrate layer with a certain thickness on the surface;
5) Numerical milling machine
Processing the profile size of the blade body of the prefabricated body deposited with the silicon carbide substrate layer according to a preset processing mathematical model and a numerical control processing program as shown in figure 1;
6) Machining of turbulence column
Cleaning the reserved gap, ensuring the reserved gap to be flat without concave and convex points, processing a turbulence column hole at the rear edge of the blade body of the prefabricated body, and riveting a SiC/SiC pin at the turbulence column hole to serve as a turbulence column; the flow disturbing column hole positions are distributed in a finished product shape at the rear edge of the blade body, the hole pitch is 8-10 mm, but the flow disturbing column hole positions are not limited to the triangular arrangement and can also be designed into a curved line array or a linear array;
7) Silicon carbide substrate deposition
Putting the riveted prefabricated body into a chemical vapor deposition furnace again, and heating at the preset temperature of 800 ℃, the pressure of 2300Pa, the time of 96h, and the flow: bubbling hydrogen gas for 7L/min, diluting argon gas for 5L/min and methyl trichlorosilane for 20L/min, depositing a silicon carbide matrix layer meeting certain density requirements on the surface of the prefabricated part, and finally obtaining the SiC/SiC ceramic composite blade body component with the micro turbulence column cooling gaps as shown in figures 2 to 4.
After the preparation is finished, the size, the appearance, the density and the strength of the obtained blade body component are tested according to the related technical requirements, and the result shows that: the size of the turbulent flow column and the blade body gap (cleft gap) is stable and controllable, and the use requirement of parts (blade body components) is met.
Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present invention, and not for limiting the same, and it is obvious for those skilled in the art to modify the specific technical solutions described in the foregoing embodiments or to substitute part of the technical features, and these modifications or substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions protected by the present invention.
Claims (5)
1. A preparation method of a SiC/SiC ceramic composite blade body component with a small turbulent flow column cooling gap is characterized by comprising the following steps:
1) Raw material selection and processing of inner and outer blade mould shaping mould
A) Selecting high-strength graphite, and processing and manufacturing an inner and outer die shaping die of the blade body;
b) Selecting SiC/SiC two-dimensional plain cloth;
2) Shaping
Shaping and sewing a prefabricated part meeting the process requirements by utilizing a shaping die of an inner die and an outer die of the blade body and adopting a two-dimensional laminating and in-situ sewing method, and reserving a gap at the vent hole of the prefabricated part;
the method is characterized in that the prefabricated body meeting the process requirements is shaped and sewn by utilizing the shaping die of the inner die and the outer die of the blade body and adopting a two-dimensional laminating and in-situ sewing method, and specifically comprises the following steps:
2.1 Winding SiC/SiC two-dimensional plain cloth on the blade body inner mold shaping mold;
2.2 Sewing the wound SiC/SiC two-dimensional plain cloth by using the silicon carbide fiber so that the SiC/SiC two-dimensional plain cloth is tightly attached to the blade body inner mold shaping mold;
2.3 Fixing the sewn SiC/SiC two-dimensional plain cloth by using an external mold, and obtaining a prefabricated body meeting the preset thickness by utilizing the gap between the internal mold and the external mold;
3) Preparation of boron nitride interface layer
Placing the prefabricated body into a chemical vapor deposition furnace, and depositing a boron nitride interface layer with a certain thickness on the fiber surface of the prefabricated body according to preset temperature, pressure, flow and time;
4) Preparation of silicon carbide substrate layer
Depositing a silicon carbide substrate layer with a certain thickness on the surface of the preform with the deposited boron nitride interface layer in a chemical vapor deposition furnace according to preset temperature, pressure, flow and time;
5) Numerical milling machine
Processing the profile size of the blade body of the prefabricated body deposited with the silicon carbide substrate layer according to a preset processing mathematical model and a numerical control processing program;
6) Turbulent flow column processing
Cleaning the reserved gap until the reserved gap is flat and free of concave-convex points, processing a turbulence column hole at the rear edge of the blade body of the prefabricated body, and riveting a SiC/SiC pin at the turbulence column hole to serve as a turbulence column;
7) Silicon carbide substrate deposition
And putting the riveted prefabricated body into the chemical vapor deposition furnace again, and depositing a silicon carbide matrix layer meeting certain density requirements on the surface of the prefabricated body according to preset temperature, pressure, flow and time to obtain the SiC/SiC ceramic composite blade body member with the micro turbulence column cooling gap.
2. The method for preparing the SiC/SiC ceramic composite blade body component with the micro spoiler column cooling gap according to claim 1, wherein the method comprises the following steps:
in step 3), the preset temperature, pressure, flow and time are specifically:
the temperature is 200-1000 ℃, the pressure is less than 1500Pa, and the time is 24-100 h;
the flow rate is as follows: the flow of diluted argon is 0.2-1.5L/min, the flow of diluted hydrogen is 0.2-1.5L/min, the flow of ammonia is 0.05-0.8L/min, and the flow of boron trichloride is 0.01-0.8L/min.
3. The method for preparing the SiC/SiC ceramic composite blade body component with the micro spoiler column cooling gap according to claim 2, wherein the method comprises the following steps:
in step 4), the preset temperature, pressure, flow and time are specifically:
the temperature is 500-1500 ℃, the pressure is less than 3500Pa, and the time is 24-180 h;
the flow rate is as follows: bubbling hydrogen gas 1-10L/min, diluting hydrogen gas 0.1-10L/min, diluting argon gas 0.1-10L/min and methyl trichlorosilane 5-70L/min.
4. The preparation method of the SiC/SiC ceramic composite blade body component with the micro turbulence column cooling gap according to claim 3, wherein the preparation method comprises the following steps:
in step 7), the preset temperature, pressure, flow and time are specifically:
the temperature is 500-1500 ℃, the pressure is less than 3500Pa, and the time is 24-180 h;
the flow rate is as follows: bubbling hydrogen gas 1-10L/min, diluting hydrogen gas 0.1-10L/min, diluting argon gas 0.1-10L/min and methyl trichlorosilane 5-70L/min.
5. The method for preparing the SiC/SiC ceramic composite blade body component with the micro spoiler column cooling gap according to claim 4, wherein the method comprises the following steps:
in the step 2), the width of the gap is 0.7mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111199678.3A CN113929467B (en) | 2021-10-14 | 2021-10-14 | Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111199678.3A CN113929467B (en) | 2021-10-14 | 2021-10-14 | Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113929467A CN113929467A (en) | 2022-01-14 |
| CN113929467B true CN113929467B (en) | 2023-02-14 |
Family
ID=79279289
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111199678.3A Active CN113929467B (en) | 2021-10-14 | 2021-10-14 | Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113929467B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115093231B (en) * | 2022-06-23 | 2023-09-01 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite guide vane with trailing edge split joint and preparation method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109736899A (en) * | 2019-01-13 | 2019-05-10 | 中国航发四川燃气涡轮研究院 | A kind of turbine blade tail with microchannel partly splits seam cooling structure |
| CN110143824A (en) * | 2019-05-29 | 2019-08-20 | 中南大学 | A kind of without residual stress homogeneous high temperature resistant type SiCfThe preparation method of/SiC turbine blisk |
| JP6569018B2 (en) * | 2016-01-13 | 2019-08-28 | エコマンダ アーゲーＥｃｏｍａｎｄａ Ａｇ | Fuel additive |
| CN111516988A (en) * | 2020-04-30 | 2020-08-11 | 中国航发北京航空材料研究院 | Protection tool for thin-wall hollow blade tail splitting seam with inner cavity provided with turbulence column structure |
| CN211715181U (en) * | 2020-03-18 | 2020-10-20 | 厦门大学 | Laminate cooling structure with slotted circular turbulence column |
| CN112279664A (en) * | 2020-11-04 | 2021-01-29 | 西安鑫垚陶瓷复合材料有限公司 | Preparation process of continuous fiber reinforced ceramic matrix composite high-strength connecting piece |
-
2021
- 2021-10-14 CN CN202111199678.3A patent/CN113929467B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6569018B2 (en) * | 2016-01-13 | 2019-08-28 | エコマンダ アーゲーＥｃｏｍａｎｄａ Ａｇ | Fuel additive |
| CN109736899A (en) * | 2019-01-13 | 2019-05-10 | 中国航发四川燃气涡轮研究院 | A kind of turbine blade tail with microchannel partly splits seam cooling structure |
| CN110143824A (en) * | 2019-05-29 | 2019-08-20 | 中南大学 | A kind of without residual stress homogeneous high temperature resistant type SiCfThe preparation method of/SiC turbine blisk |
| CN211715181U (en) * | 2020-03-18 | 2020-10-20 | 厦门大学 | Laminate cooling structure with slotted circular turbulence column |
| CN111516988A (en) * | 2020-04-30 | 2020-08-11 | 中国航发北京航空材料研究院 | Protection tool for thin-wall hollow blade tail splitting seam with inner cavity provided with turbulence column structure |
| CN112279664A (en) * | 2020-11-04 | 2021-01-29 | 西安鑫垚陶瓷复合材料有限公司 | Preparation process of continuous fiber reinforced ceramic matrix composite high-strength connecting piece |
Non-Patent Citations (1)
| Title |
|---|
| 陶瓷基复合材料及其环境障涂层发展现状研究;江舟等;《航空制造技术》;20200715(第14期);第36-52页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113929467A (en) | 2022-01-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113929467B (en) | Preparation method of SiC/SiC ceramic composite blade body component with small turbulence column cooling gap | |
| CN105817626B (en) | A kind of metal material gradient component fusion coating building mortion and method | |
| CN106825566A (en) | A kind of method that selective laser is melted and molded martensite ag(e)ing steel mold | |
| CN109386399B (en) | Structure with circuitous inner flow passage and manufacturing method thereof | |
| CN104831107B (en) | Ablation-resistant carbon/carbon-zirconium carbide-copper composite material and preparation method thereof | |
| CN107134642A (en) | A kind of resistance to 450 DEG C of quartz/composite polyimide material antenna house and preparation method | |
| CN108545914B (en) | Preparation method of anti-peeling pyrolytic boron nitride coating hot bending die for solving oxidation problem | |
| CN105296897A (en) | Method for preparing carbon fiber enhanced titanium alloy composite material | |
| CN112125679A (en) | Method for preparing omega-shaped stringer based on precursor impregnation cracking process | |
| CN114014680A (en) | Ceramic matrix composite material turbine outer ring and preparation method thereof | |
| CN103286919B (en) | A kind of mould through graphenic surface process and preparation method thereof | |
| CN107433670A (en) | The preparation method of mobile communication equipment shell | |
| CN101705446A (en) | Preparation technology of titanium carbide reinforced high-speed steel base composite material | |
| WO2018023168A1 (en) | A multi material laminated tool having improved thermal coupling | |
| CN206999537U (en) | A kind of block ventilation body embedding die of assembled arrangement formula | |
| CN115157516A (en) | Preparation method of novel carbon fiber insulation board | |
| CN110303693A (en) | A kind of compression-moulding methods of small-sized aerofoil Composite Sandwich part | |
| CN217617592U (en) | Titanium alloy graphite mold casting mould | |
| CN113898417A (en) | Ceramic matrix composite turbine guide blade with turbulence structure and preparation method thereof | |
| CN112125673A (en) | Method for preparing right-angle stringer based on precursor impregnation cracking process | |
| CN104193422A (en) | Silicon carbide ceramic mold core for glass modeling and preparation method thereof | |
| CN106194378A (en) | A kind of Novel exhaust manifold heat shield and manufacture method thereof | |
| CN114835500B (en) | Preparation method of variable-curvature reinforced member made of SiC/SiC composite material | |
| CN109228052B (en) | Method for manufacturing cooling pipeline in heat dissipation component | |
| CN115838294B (en) | Preparation method of ceramic matrix composite regulating sheet or sealing sheet and shaping die |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 710117 West Section 912 of Biyuan Road, Xi'an High-tech Zone, Shaanxi Province Patentee after: Xi'an Xinyao Ceramic Composite Co.,Ltd. Country or region after: China Address before: 710117 West Section 912 of Biyuan Road, Xi'an High-tech Zone, Shaanxi Province Patentee before: XI'AN GOLDEN MOUNTAIN CERAMIC COMPOSITES CO.,LTD. Country or region before: China |