CN114014680A - A kind of ceramic matrix composite turbine outer ring and preparation method thereof - Google Patents
A kind of ceramic matrix composite turbine outer ring and preparation method thereof Download PDFInfo
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- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 58
- 238000002360 preparation method Methods 0.000 title claims abstract description 28
- 239000000835 fiber Substances 0.000 claims abstract description 42
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims abstract description 33
- 229910010271 silicon carbide Inorganic materials 0.000 claims abstract description 33
- 238000000034 method Methods 0.000 claims abstract description 32
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 27
- 239000000919 ceramic Substances 0.000 claims abstract description 26
- 229910002804 graphite Inorganic materials 0.000 claims abstract description 24
- 239000010439 graphite Substances 0.000 claims abstract description 24
- 239000000463 material Substances 0.000 claims abstract description 23
- 229910052582 BN Inorganic materials 0.000 claims abstract description 21
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims abstract description 21
- 238000009941 weaving Methods 0.000 claims abstract description 21
- 238000005229 chemical vapour deposition Methods 0.000 claims abstract description 16
- 238000000151 deposition Methods 0.000 claims abstract description 14
- 239000011265 semifinished product Substances 0.000 claims abstract description 13
- 239000002994 raw material Substances 0.000 claims abstract description 12
- 239000000758 substrate Substances 0.000 claims abstract description 8
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 28
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 14
- 229910052786 argon Inorganic materials 0.000 claims description 14
- 239000011159 matrix material Substances 0.000 claims description 14
- 239000007789 gas Substances 0.000 claims description 13
- 239000001257 hydrogen Substances 0.000 claims description 13
- 229910052739 hydrogen Inorganic materials 0.000 claims description 13
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 claims description 9
- DWAWYEUJUWLESO-UHFFFAOYSA-N trichloromethylsilane Chemical compound [SiH3]C(Cl)(Cl)Cl DWAWYEUJUWLESO-UHFFFAOYSA-N 0.000 claims description 9
- 238000004321 preservation Methods 0.000 claims description 8
- 238000005137 deposition process Methods 0.000 claims description 7
- 238000003754 machining Methods 0.000 claims description 6
- FAQYAMRNWDIXMY-UHFFFAOYSA-N trichloroborane Chemical compound ClB(Cl)Cl FAQYAMRNWDIXMY-UHFFFAOYSA-N 0.000 claims description 5
- 238000005452 bending Methods 0.000 claims description 4
- 230000008021 deposition Effects 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 238000009954 braiding Methods 0.000 claims 3
- 239000010410 layer Substances 0.000 abstract description 17
- 239000011229 interlayer Substances 0.000 abstract description 5
- 229910052799 carbon Inorganic materials 0.000 abstract description 3
- 239000000047 product Substances 0.000 abstract description 2
- 230000000052 comparative effect Effects 0.000 description 10
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- 238000007493 shaping process Methods 0.000 description 6
- 238000001816 cooling Methods 0.000 description 5
- 229910021529 ammonia Inorganic materials 0.000 description 4
- 239000002131 composite material Substances 0.000 description 4
- 238000004132 cross linking Methods 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 239000004744 fabric Substances 0.000 description 3
- 238000009958 sewing Methods 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000000280 densification Methods 0.000 description 2
- 238000000626 liquid-phase infiltration Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000011056 performance test Methods 0.000 description 2
- 239000011226 reinforced ceramic Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- AFCARXCZXQIEQB-UHFFFAOYSA-N N-[3-oxo-3-(2,4,6,7-tetrahydrotriazolo[4,5-c]pyridin-5-yl)propyl]-2-[[3-(trifluoromethoxy)phenyl]methylamino]pyrimidine-5-carboxamide Chemical compound O=C(CCNC(=O)C=1C=NC(=NC=1)NCC1=CC(=CC=C1)OC(F)(F)F)N1CC2=C(CC1)NN=N2 AFCARXCZXQIEQB-UHFFFAOYSA-N 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000011895 specific detection Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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- 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
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- 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
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- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
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- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
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- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- C04B2235/38—Non-oxide ceramic constituents or additives
- C04B2235/3852—Nitrides, e.g. oxynitrides, carbonitrides, oxycarbonitrides, lithium nitride, magnesium nitride
- C04B2235/386—Boron nitrides
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Abstract
The invention discloses a ceramic matrix composite turbine outer ring and a preparation method thereof, wherein the preparation method of the turbine outer ring comprises the following steps: weaving the fiber preform by using carbon-containing fibers as raw materials and adopting a 2.5-dimensional weaving method; preparing a turbine outer ring mold by taking graphite as a raw material; placing the fiber preform into a mold, and sequentially depositing a boron nitride interface layer and a silicon carbide substrate by adopting a chemical vapor deposition method to prepare a ceramic matrix composite material turbine outer ring blank; and then depositing silicon carbide ceramics on the surface of the ceramic matrix composite material turbine outer ring semi-finished product to obtain the ceramic matrix composite material turbine outer ring finished product. The ceramic matrix composite turbine outer ring can effectively solve the problem that the interlayer bonding strength of the existing turbine outer ring is weak.
Description
Technical Field
The invention belongs to the technical field of engine manufacturing, and particularly relates to a ceramic matrix composite turbine outer ring and a preparation method thereof.
Background
The turbine outer ring is one of the key structural components of the turbine system of the engine, and the main function of the turbine outer ring is to form a gas channel. The turbine outer ring is arranged on the turbine casing, correspondingly arranged around the turbine rotor blades and matched with the corresponding turbine rotor blade tips in pairs to form a radial gap between the rotating part and the casing. With the continuous development of advanced engines, the requirements of higher temperature resistance, longer service life and lighter weight are put on the turbine outer ring component.
At present, nickel-based and cobalt-based high-temperature alloy materials adopted by a turbine outer ring are difficult to meet the high-temperature creep strength and high-temperature oxidation and corrosion resistance which are necessary for safe and reliable operation of a next-generation advanced engine, and the structural weight reduction requirement of the engine. As a thermal structure function integrated material with the advantages of various materials such as low density, high temperature resistance, oxidation resistance, corrosion resistance, high toughness and the like, the ceramic matrix composite material is considered to be one of the most potential materials for developing advanced high-temperature components of engines by the international public and can well meet the use requirements of turbine outer ring members.
At present, the outer ring of the ceramic matrix composite turbine mainly adopts a preform molding mode of two-dimensional woven cloth lamination sewing and a ceramic matrix densification mode of melt infiltration. However, with the improvement of the use requirement of the advanced engine on the turbine outer ring, the requirement on the interlayer bonding strength of the material is higher and higher, and when the prefabricated part forming mode and the ceramic matrix densification mode are adopted for component preparation, the interlayer bonding strength of the structure is weaker, and the temperature resistance is lower.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides the ceramic matrix composite turbine outer ring and the preparation method thereof, and the ceramic matrix composite turbine outer ring can effectively solve the problems of weak interlayer bonding strength and low temperature resistance of the conventional turbine outer ring.
In order to achieve the purpose, the technical scheme adopted by the invention for solving the technical problems is as follows:
a preparation method of a ceramic matrix composite turbine outer ring comprises the following steps:
(1) weaving the fiber preform by using carbon-containing fibers as raw materials and adopting a 2.5-dimensional weaving method;
(2) preparing a turbine outer ring mold by taking graphite as a raw material;
(3) placing the fiber preform in the step (1) into the mold in the step (2), and depositing a boron nitride interface layer and a silicon carbide substrate in sequence by adopting a chemical vapor deposition method to prepare a ceramic matrix composite material turbine outer ring blank;
(4) and (4) mechanically processing the ceramic matrix composite material turbine outer ring blank in the step (3) to obtain a ceramic matrix composite material turbine outer ring semi-finished product, and then depositing silicon carbide ceramic on the surface of the ceramic matrix composite material turbine outer ring semi-finished product to obtain the ceramic matrix composite material turbine outer ring finished product.
Further, the carbon-containing fiber in the step (1) is carbon fiber and/or silicon carbide fiber.
Further, the 2.5-dimensional weaving method in the step (1) is 2.5-dimensional shallow cross-bending combined weaving or 2.5-dimensional deep cross-bending combined weaving.
Further, the graphite in the step (2) is electrode graphite or high-purity graphite.
Further, the preparation process of the boron nitride interface layer in the step (3) is as follows: heating to 650-1000 ℃ under the condition that the pressure in the furnace body is 50-1000Pa, preserving heat for 1-2h, then sequentially introducing argon, hydrogen, ammonia and boron trichloride gas, depositing for 15-35h, then preserving heat for 2h, and cooling to room temperature.
Further, the boron nitride interface layer deposition process in the step (3) is performed 1-3 times.
Further, the thickness of the boron nitride interface layer in step (3) is 150-750 nm.
Further, the preparation process of the silicon carbide substrate in the step (3) is as follows: heating to 900-1200 ℃ under the condition that the pressure in the furnace body is 200-5000Pa, keeping the temperature for 1-2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon, depositing for 30-80h, then keeping the temperature for 2h, and cooling to the room temperature.
Further, the deposition process of the silicon carbide substrate in the step (3) is performed 4 to 8 times.
Further, the density of the ceramic matrix composite material turbine outer ring semi-finished product in the step (4) is 2.2-2.4g/cm3The density of the final ceramic matrix composite turbine outer ring is 2.45-2.75g/cm3。
The beneficial effect that above-mentioned scheme produced does:
1. compared with the traditional two-dimensional woven cloth laminated prefabricated body sewing mode, the 2.5-dimensional weaving method adopted by the invention greatly improves the prefabricated body forming efficiency and reduces the preparation period and cost; meanwhile, due to the cross-linking strengthening effect of the 2.5-dimensional fiber preform in the thickness direction of the outer ring of the turbine, the interlayer bonding strength of the outer ring member of the turbine is improved from 40MPa to 60 MPa.
2. The method for preparing the silicon carbide ceramic matrix by adopting the chemical vapor deposition process can improve the tensile strength of the outer ring member of the turbine from 240MPa to 330MPa and the long-term temperature resistance from 1200 ℃ to 1350 ℃.
Drawings
FIG. 1 is a flow chart of the outer ring preparation of the ceramic matrix composite turbine of the present invention;
FIG. 2 is a photograph of a finished outer ring of the ceramic matrix composite turbine according to example 1.
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings.
Example 1
The preparation method of the ceramic matrix composite turbine outer ring comprises the following steps:
(1) weaving of the fiber preform: taking third-generation silicon carbide fiber as a raw material, and weaving a fiber preform by adopting a 2.5-dimensional shallow cross-linking weaving method according to the structure and the shape and the size of a turbine outer ring;
(2) designing and manufacturing a die: the method comprises the following steps of designing and preparing a graphite mold according to the structure, shape and size of a turbine outer ring prefabricated body by taking high-purity graphite as a raw material, wherein the inner cavity structure of the mold is consistent with the outer ring structure of the turbine, and a plurality of vent holes are formed in the surface of the mold;
(3) shaping of the fiber preform: placing the fiber preform into the graphite mold for fixing to realize the shaping of the fiber preform;
(4) preparing an interface layer: placing a graphite mold with a fiber preform in a boron nitride chemical vapor deposition furnace, wherein gas penetrates through a vent hole to enter the mold, and preparing a boron nitride interface layer on the surface of the fiber preform, wherein the specific deposition process is as follows: the pressure in the furnace body is 500Pa, the temperature is raised to 650 ℃, after 2h of heat preservation, argon, hydrogen, ammonia and boron trichloride gas are sequentially introduced, the heat preservation is continued for 2h after 30h of deposition, the temperature is reduced to room temperature, and then the step is repeatedly executed for 2 times, so that the thickness of the boron nitride interface layer is 380 nm;
(5) preparing a ceramic matrix: putting the fiber preform deposited with the boron nitride interface layer in the step (4) and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, wherein the specific preparation process comprises the following steps: and (3) heating the pressure in the furnace body to 1000Pa, keeping the temperature for 2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon, wherein the flow ratio of trichloromethylsilane to hydrogen to argon is 1: 15: 20, depositing for 80 hours, keeping the temperature for 2 hours, cooling to room temperature, and repeatedly executing the steps for 6 times to obtain the ceramic matrix composite material turbine outer ring blank;
(6) and (3) machining: according to a design drawing, mechanically processing the outer ring blank of the ceramic matrix composite turbine to a required size to obtain a semi-finished product of the outer ring of the ceramic matrix composite turbine;
(7) repairing processing damage: and (3) placing the semi-finished product of the outer ring of the ceramic matrix composite turbine in a silicon carbide chemical vapor deposition furnace, covering silicon carbide ceramic on all processing surfaces of the outer ring of the turbine, wherein the silicon carbide chemical vapor deposition process parameters used in the step are consistent with the process parameters in the step (5), and repeating the step for 2 times to obtain the outer ring of the ceramic matrix composite turbine.
Example 2
The preparation method of the ceramic matrix composite turbine outer ring comprises the following steps:
(1) weaving of the fiber preform: taking third-generation silicon carbide fiber as a raw material, and weaving a fiber preform by adopting a 2.5-dimensional deep cross-linking weaving method according to the structure and the shape and the size of a turbine outer ring;
(2) designing and manufacturing a die: designing and preparing a graphite mold according to the structure, shape and size of a turbine outer ring preform by taking electrode graphite as a raw material, wherein the structure of an inner cavity of the mold is consistent with that of a turbine outer ring;
(3) shaping of the fiber preform: placing the fiber preform into the graphite mold for fixing to realize the shaping of the fiber preform;
(4) preparing an interface layer: placing a graphite mold clamped with a fiber preform in a boron nitride chemical vapor deposition furnace, and preparing a boron nitride interface layer on the surface of the fiber preform, wherein the specific deposition process comprises the following steps: the pressure in the furnace body is 1000Pa, the temperature is raised to 1000 ℃, after heat preservation is carried out for 1h, argon, hydrogen, ammonia and boron trichloride gas are sequentially introduced, heat preservation is continued for 2h after deposition is carried out for 20h, the temperature is reduced to room temperature, and then the steps are repeatedly carried out for 3 times, so that the thickness of the boron nitride interface layer is 490 nm;
(5) preparing a ceramic matrix: putting the fiber preform deposited with the boron nitride interface layer in the step (4) and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, wherein the specific preparation process comprises the following steps: and (3) heating the pressure in the furnace body to 800 ℃ under the pressure of 1000Pa, keeping the temperature for 2 hours, introducing mixed gas of trichloromethylsilane, hydrogen and argon, wherein the flow ratio of trichloromethylsilane to hydrogen to argon is 1: 10: 15, depositing for 60 hours, keeping the temperature for 2 hours, cooling to room temperature, and repeatedly executing the steps for 6 times to obtain the ceramic matrix composite material turbine outer ring blank;
(6) and (3) machining: according to a design drawing, machining the outer ring blank of the ceramic matrix composite turbine to a required size to obtain a semi-finished product of the outer ring of the ceramic matrix composite turbine;
(7) repairing processing damage: and (3) placing the semi-finished product of the outer ring of the ceramic matrix composite turbine in a silicon carbide chemical vapor deposition furnace, covering silicon carbide ceramic on all processing surfaces of the outer ring of the turbine, wherein the silicon carbide chemical vapor deposition process parameters used in the step are consistent with the process parameters in the step (5), and repeating the step for 3 times to obtain the outer ring of the ceramic matrix composite turbine.
Example 3
The preparation method of the ceramic matrix composite turbine outer ring comprises the following steps:
(1) weaving of the fiber preform: taking third-generation silicon carbide fiber as a raw material, and weaving a fiber preform by adopting a 2.5-dimensional shallow cross-linking weaving method according to the structure and the shape and the size of a turbine outer ring;
(2) designing and manufacturing a die: designing and preparing a graphite mold according to the structure, shape and size of a turbine outer ring preform by taking high-purity graphite as a raw material, wherein the structure of an inner cavity of the mold is consistent with that of a turbine outer ring;
(3) shaping of the fiber preform: placing the fiber preform into the graphite mold for fixing to realize the shaping of the fiber preform;
(4) preparing an interface layer: placing a graphite mold clamped with a fiber preform in a boron nitride chemical vapor deposition furnace, and preparing a boron nitride interface layer on the surface of the fiber preform, wherein the specific deposition process comprises the following steps: the pressure in the furnace body is 800Pa, the temperature is raised to 800 ℃, after heat preservation is carried out for 2h, argon, hydrogen, ammonia and boron trichloride gas are sequentially introduced, heat preservation is continued for 2h after deposition is carried out for 25h, the temperature is reduced to room temperature, and then the steps are repeatedly carried out for 3 times, so that the thickness of the boron nitride interface layer is 430 nm;
(5) preparing a ceramic matrix: putting the fiber preform deposited with the boron nitride interface layer in the step (4) and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, wherein the specific preparation process comprises the following steps: the pressure in the furnace body is 1500Pa, the temperature is raised to 900 ℃, after 2h of heat preservation, mixed gas of trichloromethyl silane, hydrogen and argon is introduced, and the flow ratio of trichloromethyl silane to hydrogen to argon is 1: 7: 12, depositing for 80 hours, keeping the temperature for 2 hours, cooling to room temperature, and repeatedly executing the steps for 8 times to obtain the ceramic matrix composite material turbine outer ring blank;
(6) and (3) machining: according to a design drawing, machining the outer ring blank of the ceramic matrix composite turbine to a required size to obtain a semi-finished product of the outer ring of the ceramic matrix composite turbine;
(7) repairing processing damage: and (3) placing the semi-finished product of the outer ring of the ceramic matrix composite turbine in a silicon carbide chemical vapor deposition furnace, covering silicon carbide ceramic on all processing surfaces of the outer ring of the turbine, wherein the silicon carbide chemical vapor deposition process parameters used in the step are consistent with the process parameters in the step (5), and repeating the step for 2 times to obtain the outer ring of the ceramic matrix composite turbine.
Comparative example 1
Compared with the preparation method of the outer ring of the ceramic matrix composite turbine in the embodiment 1, the silicon carbide substrate is prepared by adopting a reaction melt infiltration method.
Comparative example 2
Compared with the embodiment 1, the preparation method of the ceramic matrix composite turbine outer ring adopts a two-dimensional woven cloth laminated sewing preform.
Test examples
The density of the ceramic-based turbine outer ring semi-finished product and the ceramic-based turbine outer ring obtained in the examples 1-3 and the comparative examples 1-2 is detected respectively, and the specific detection process execution standard is as follows: the GB/T2997-. The interlaminar shear properties of the outer ring of the ceramic matrix turbine of examples 1-3 and comparative examples 1-2 were measured using the Q/AVIC 06185.4-2015 continuous fiber reinforced ceramic matrix composite high temperature mechanical testing method part 4: the interlaminar shear performance test method has the specific measurement results shown in the table 1; the tensile strength of the ceramic-based turbine outer ring in examples 1 to 3 and comparative examples 1 to 2 was measured by the following specific measurement criteria: Q/AVIC 06185.1-2015 continuous fiber reinforced ceramic matrix composite high temperature mechanical Properties test method part 1: the tensile properties were tested and the results are shown in Table 1.
Table 1: ceramic-based turbine outer ring performance test
| Density (g/cm3) | Interlaminar shear strength (MPa) | Tensile Strength (MPa) | Temperature resistance (. degree. C.) | |
| Example 1 | 2.62 | 60 | 322 | 1350 |
| Example 2 | 2.59 | 56 | 320 | 1350 |
| Example 3 | 2.61 | 57 | 321 | 1350 |
| Comparative example 1 | 2.68 | 48 | 240 | 1200 |
| Comparative example 2 | 2.45 | 40 | 310 | 1350 |
The data in the table show that the strength and the temperature resistance of the ceramic-based turbine outer ring prepared by the method in the embodiment 1-3 are superior to those of the ceramic-based turbine outer ring in the comparative example 1-2, and the interlaminar shear strength, the tensile strength and the temperature resistance of the ceramic-based composite turbine outer ring are reduced by changing the preparation method of the silicon carbide substrate in the comparative example 1, so that the forming method of the silicon carbide ceramic substrate has great influence on the performance of the ceramic-based composite turbine outer ring; in comparative example 2, the density and the interlaminar shear strength of the outer ring of the CMC turbine are reduced by changing the weaving method of the fiber preform, which proves that the weaving mode of the fiber preform also has a great influence on the performance of the outer ring of the CMC turbine.
Claims (10)
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