CN114315396B - Ceramic matrix composite turbine outer ring with abradable coating and preparation method thereof - Google Patents
Ceramic matrix composite turbine outer ring with abradable coating and preparation method thereof Download PDFInfo
- Publication number
- CN114315396B CN114315396B CN202111592822.XA CN202111592822A CN114315396B CN 114315396 B CN114315396 B CN 114315396B CN 202111592822 A CN202111592822 A CN 202111592822A CN 114315396 B CN114315396 B CN 114315396B
- Authority
- CN
- China
- Prior art keywords
- outer ring
- ceramic matrix
- matrix composite
- preparing
- abradable coating
- 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
- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 100
- 239000011248 coating agent Substances 0.000 title claims abstract description 60
- 238000000576 coating method Methods 0.000 title claims abstract description 60
- 238000002360 preparation method Methods 0.000 title claims abstract description 35
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 44
- 239000000835 fiber Substances 0.000 claims description 42
- 239000011159 matrix material Substances 0.000 claims description 40
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 35
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 35
- 238000000034 method Methods 0.000 claims description 32
- 229910052582 BN Inorganic materials 0.000 claims description 28
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims description 28
- 238000000151 deposition Methods 0.000 claims description 28
- 239000011265 semifinished product Substances 0.000 claims description 28
- 229910052786 argon Inorganic materials 0.000 claims description 22
- 239000001257 hydrogen Substances 0.000 claims description 22
- 229910052739 hydrogen Inorganic materials 0.000 claims description 22
- 239000000919 ceramic Substances 0.000 claims description 21
- 238000003754 machining Methods 0.000 claims description 21
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 18
- 239000007789 gas Substances 0.000 claims description 17
- 229910003460 diamond Inorganic materials 0.000 claims description 16
- 239000010432 diamond Substances 0.000 claims description 16
- 239000000463 material Substances 0.000 claims description 15
- 238000001816 cooling Methods 0.000 claims description 14
- DWAWYEUJUWLESO-UHFFFAOYSA-N trichloromethylsilane Chemical compound [SiH3]C(Cl)(Cl)Cl DWAWYEUJUWLESO-UHFFFAOYSA-N 0.000 claims description 14
- 238000010438 heat treatment Methods 0.000 claims description 13
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 claims description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 12
- 238000005229 chemical vapour deposition Methods 0.000 claims description 12
- 230000008021 deposition Effects 0.000 claims description 12
- 229910002804 graphite Inorganic materials 0.000 claims description 12
- 239000010439 graphite Substances 0.000 claims description 12
- 238000012545 processing Methods 0.000 claims description 11
- FAQYAMRNWDIXMY-UHFFFAOYSA-N trichloroborane Chemical compound ClB(Cl)Cl FAQYAMRNWDIXMY-UHFFFAOYSA-N 0.000 claims description 8
- 238000013461 design Methods 0.000 claims description 6
- 238000012986 modification Methods 0.000 claims description 6
- 230000004048 modification Effects 0.000 claims description 6
- 238000007750 plasma spraying Methods 0.000 claims description 6
- 238000004321 preservation Methods 0.000 claims description 6
- 239000002994 raw material Substances 0.000 claims description 6
- 238000009941 weaving Methods 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 229910021529 ammonia Inorganic materials 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 230000007547 defect Effects 0.000 abstract description 2
- 238000004381 surface treatment Methods 0.000 description 10
- 230000000052 comparative effect Effects 0.000 description 8
- 238000004154 testing of material Methods 0.000 description 5
- 239000000446 fuel Substances 0.000 description 4
- 150000002431 hydrogen Chemical class 0.000 description 4
- 230000003647 oxidation Effects 0.000 description 4
- 238000007254 oxidation reaction Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000007796 conventional method Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003153 chemical reaction reagent Substances 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
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
-
- 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
Abstract
The invention provides a ceramic matrix composite turbine outer ring with an abradable coating and a preparation method thereof, and overcomes the defect of weak bonding force between the existing ceramic matrix composite turbine outer ring and the abradable coating.
Description
Technical Field
The invention relates to a preparation method of a turbine outer ring of a gas turbine engine, in particular to a ceramic matrix composite turbine outer ring with an abradable coating and a preparation method thereof.
Background
With the development of military aviation, the requirements on the aero-engine are higher and higher, wherein the most important is to improve the thrust-weight ratio and the fuel efficiency so that the advanced aero-engine has good air path sealing performance. For a gas turbine engine, the most key for improving the thrust-weight ratio is to reduce the weight and improve the temperature before the turbine, so that the requirements on the light weight and high-temperature performance of internal components of the engine are higher and higher, and the key for improving the thrust-weight ratio and the fuel efficiency is to use the turbine outer ring as a turbine stator part.
At present, nickel-based and cobalt-based high-temperature alloy materials adopted by a turbine outer ring are difficult to meet the weight reduction requirement of the next generation of advanced engine structures. 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 light requirement of turbine outer ring members so as to improve the thrust-weight ratio.
At present, the preparation of carrying out the abradable coating on turbine outer ring surface can effectively regulate and control the clearance of engine rotor and stator, improves fuel efficiency, nevertheless because the great messenger's cohesion between abradable coating and the ceramic matrix composite turbine outer ring is weak between the two, drops easily under the scratch and the thermal shock condition.
Disclosure of Invention
In order to overcome the defect of weak bonding force between the outer ring of the existing ceramic matrix composite turbine and the abradable coating, the invention provides a preparation method of the outer ring of the ceramic matrix composite turbine with the abradable coating and the outer ring of the ceramic matrix composite turbine with the abradable coating prepared by the preparation method.
The technical scheme of the invention is as follows:
the preparation method of the ceramic matrix composite turbine outer ring with the abradable coating is characterized by comprising the following steps:
step 1, preparing a ceramic matrix composite turbine outer ring semi-finished product;
step 1.1, preparing a fiber preform: carbon fiber or silicon carbide fiber or a combination of the carbon fiber and the silicon carbide fiber is taken as a raw material, and a fiber preform is obtained by adopting a two-dimensional weaving method according to the structure, the shape and the size of the outer ring of the turbine;
step 1.2, preparing an interface layer: clamping the fiber preform by using a graphite mold, placing the 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 step may need to be executed for 1-4 times in a circulating manner;
step 1.3, preparation of a ceramic matrix: placing the fiber preform deposited with the boron nitride interface layer in the step 1.2 and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, wherein the step may need to be executed circularly for 4-8 times to obtain a ceramic matrix composite material turbine outer ring blank;
step 1.4, 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;
step 2.1, shallow hole processing: fixing the ceramic matrix composite turbine outer ring semi-finished product on a positioning tool, and processing shallow holes with set depth on the surface of the ceramic matrix composite turbine outer ring semi-finished product according to a certain arrangement sequence;
step 2.2, deposition of CVI: depositing a SiC matrix on the ceramic matrix composite material turbine outer ring matrix treated in the step 2.1 to obtain a surface treated ceramic matrix composite material turbine outer ring;
step 3, preparing an abradable coating;
and preparing an abradable coating on the surface of the shallow hole machined in the outer ring of the ceramic matrix composite turbine.
Further, in step 1.2, the preparation process parameters of the boron nitride interface layer are as follows: the pressure in the furnace body is 40-850Pa, the temperature is raised to 700-1000 ℃, after heat preservation is carried out for 1-2h, argon, hydrogen, ammonia and boron trichloride gas are sequentially introduced, deposition is carried out for 15-35h, heat preservation is carried out for 2h, and the temperature is reduced to room temperature.
Further, the thickness of the boron nitride interface layer on the surface of the fiber preform is 120-650nm.
Further, in step 1.3, the preparation process parameters of the silicon carbide ceramic matrix are as follows: the pressure in the furnace body is 200-5000Pa, the temperature is raised to 950-1200 ℃, the temperature is kept for 1-2h, then mixed gas of trichloromethyl silane, hydrogen and argon is introduced, the flow ratio of trichloromethyl silane, hydrogen and argon is 1: 5-20: 10-25, the deposition is carried out for 30-80h, the temperature is kept for 2h, and the temperature is reduced to room temperature.
Further, in the step 2.1, a diamond drill is selected to process shallow holes on the surface of the ceramic matrix composite turbine outer ring semi-finished product, the shallow holes are round holes with the depth equal to 0.5mm and the diameter equal to 0.8-1.5mm, the latitudinal direction is uniformly arranged on the surface of the turbine outer ring according to the sequence that the distance between every two rows of holes is 2.8-3.8 mm, and the longitudinal direction is arranged according to the distance of 2 degrees.
Further, in the step 3, the abradable coating is prepared by mixing BSAS and PHB according to a certain volume ratio and then coating by using a plasma spraying method, wherein the thickness range of the abradable coating is 0.95mm-1.5mm. The turbine outer ring with the shallow hole machined on the surface is prepared according to the concrete implementation steps, and the abradable coating is prepared on the turbine outer ring.
Further, in step 1.2, the preparation process parameters of the boron nitride interface layer are as follows: heating the furnace body to the pressure of 500Pa, keeping the temperature for 2h, sequentially introducing argon, hydrogen, ammonia and boron trichloride gas, depositing for 30h, keeping the temperature for 2h, and cooling to room temperature; in the step 1.3, the preparation process parameters of the silicon carbide ceramic matrix are as follows: heating the furnace body to the pressure of 350Pa, heating to 1200 ℃, keeping the temperature for 1-2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon, depositing for 80h, keeping the temperature for 2h, and cooling to the room temperature; in the step 2.1, the shallow holes are round holes with the depth equal to 0.5mm and the diameter equal to 1.3mm, the latitudinal directions are uniformly arranged on the surface of the outer ring of the turbine according to the sequence of the spacing of 3.0mm between every two rows of holes, and the longitudinal directions are arranged at the spacing of 2 degrees.
The invention also provides the ceramic matrix composite turbine outer ring with the abradable coating prepared by the preparation method.
The invention has the advantages and beneficial effects that:
1. the invention provides a surface treatment method of an outer ring of a ceramic matrix composite turbine, which increases the contact area between a coating and a base body and effectively improves the bonding strength between the base body and the coating by performing shallow hole machining on the surface of the outer ring of the ceramic matrix composite turbine, wherein the bonding strength of the outer ring of the turbine is improved from 3.313MPa which is not subjected to surface treatment to 9.532MPa of surface shallow hole machining.
2. The method for SiC deposition after shallow hole processing can effectively reduce the damage to fibers, improve the service efficiency and fuel efficiency of the outer ring of the turbine, and increase the long-time temperature resistance of the outer ring of the turbine from 1200 ℃ to 1350 ℃.
3. According to the invention, shallow holes with different sizes are processed on the surface of the outer ring of the ceramic matrix composite turbine, the relation between relevant parameters of the shallow holes and the bonding strength is researched, and finally the depth, the hole type and the diameter of the shallow holes are determined as main influence factors. And finally determining the depth, the hole type, the diameter and the arrangement mode of the better shallow holes through a large number of experimental researches, and further improving the bonding strength between the surface of the outer ring of the ceramic matrix composite turbine and the abradable coating.
Drawings
FIG. 1 is a schematic view illustrating the machining of a shallow hole on the surface of an outer ring of a ceramic matrix composite turbine according to the present invention;
FIG. 2 is a pictorial view of the abradable coating sprayed on the surface of the ceramic matrix composite turbine outer ring after machining;
FIG. 3 is a graph comparing the bond strength of an untreated and a treated outer ring of a ceramic matrix composite turbine of the present invention. Wherein a is not surface-treated, and b is surface-treated.
Detailed Description
The following detailed description of specific embodiments of the invention is provided, but it should be understood that the scope of the invention is not limited to the specific embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention. The experimental methods described in the examples of the present invention are all conventional methods unless otherwise specified.
The following experimental methods and detection methods, unless otherwise specified, are conventional methods; the following reagents and starting materials are all commercially available unless otherwise specified.
Example 1
This example prepared a ceramic matrix composite turbine outer ring with an abradable coating by the following method:
step 1, preparing a semi-finished product of the ceramic matrix composite turbine outer ring;
step 1.1, preparing a fiber preform: in the embodiment, third-generation silicon carbide fiber is used as a raw material, and a fiber preform is obtained by adopting a two-dimensional weaving method according to the structure and the shape and the size of a turbine outer ring;
step 1.2, preparing an interface layer: and (3) placing the graphite mold with the fiber preform in a boron nitride chemical vapor deposition furnace, and preparing a boron nitride interface layer with the thickness of 450nm on the surface of the fiber preform. The preparation process parameters of the boron nitride interface layer are as follows: and (3) heating the pressure in the furnace body to 700 Pa, keeping the temperature for 2h, sequentially introducing argon, hydrogen, ammonia gas and boron trichloride gas, depositing for 30h, keeping the temperature for 2h, and cooling to room temperature. This step was repeated 2 times;
step 1.3, preparation of a ceramic matrix: placing the fiber preform deposited with the boron nitride interface layer in the step 1.2 and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, wherein the preparation process parameters of the silicon carbide ceramic matrix are as follows: and (3) heating the pressure in the furnace body to 1200 ℃ at 350Pa, keeping the temperature for 1-2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon, wherein the flow ratio of trichloromethylsilane to hydrogen to argon is 1: 15: 20, depositing for 80h, keeping the temperature for 2h, and cooling to room temperature. The step is repeatedly executed for 6 times to obtain the outer ring blank of the ceramic matrix composite turbine;
step 1.4, 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;
step 2.1, shallow hole processing: fixing the semi-finished product of the outer ring of the ceramic matrix composite turbine on a positioning tool, selecting a 45-degree diamond screwer with the thickness of 1mm, uniformly arranging the diamond screwer on the surface of the outer ring of the turbine in the weft direction according to the sequence of the spacing of 3.0mm between each row of holes, and arranging the diamond screwer in the warp direction according to the spacing of 2 degrees, wherein circular holes with the depth of 0.5mm and the diameter of 1.3mm are uniformly processed on the surface of the outer ring of the turbine in a certain arrangement sequence; note: this arrangement is due to the fact that the turbine outer ring surface is a circular arc profile, where the surface is referred to as the contact surface with the rotor blades, see in particular fig. 1.
Step 2.2, deposition by CVI: depositing a SiC matrix on the surface-modified ceramic matrix composite turbine outer ring matrix to obtain the surface-treated ceramic matrix composite turbine outer ring matrix with the density of 2.6g/cm 3 The ceramic matrix composite turbine outer ring.
Step 3, preparation of abradable coating
And preparing an abradable coating on the surface-modified ceramic matrix composite turbine outer ring by a plasma spraying method, wherein the abradable coating system comprises BSAS and PHB. As shown in FIG. 2, it can be seen that the shallow holes are still clearly visible after the coating is prepared (note: the through holes in FIG. 2 are component film holes for cooling).
The bonding force between the outer ring of the ceramic matrix composite turbine and the abradable coating in the embodiment is detected by a universal material testing machine, and as can be seen from fig. 3, the bonding strength of the outer ring of the turbine is improved from 3.313MPa which is not subjected to surface treatment to 9.532MPa which is subjected to surface shallow hole machining. Therefore, by the surface treatment method of the ceramic matrix composite turbine outer ring, the binding force between the matrix and the abradable coating can be greatly improved, and the turbine outer ring with better mechanical property and oxidation resistance can be obtained.
Example 2
This example prepared a ceramic matrix composite turbine outer ring with an abradable coating by the following method:
step 1, preparing a semi-finished product of the ceramic matrix composite turbine outer ring;
step 1.1, preparing a fiber preform: in the embodiment, third-generation silicon carbide fiber is used as a raw material, and a fiber preform is obtained by adopting a two-dimensional weaving method according to the structure and the shape and the size of a turbine outer ring;
step 1.2, preparing an interface layer: and (3) placing the graphite mould clamped with the fiber preform in a boron nitride chemical vapor deposition furnace, and preparing a boron nitride interface layer with the thickness of 650nm on the surface of the fiber preform. The preparation process parameters of the boron nitride interface layer are as follows: and (3) heating the pressure in the furnace body to 1000 Pa, keeping the temperature for 2h, sequentially introducing argon, hydrogen, ammonia gas and boron trichloride gas, depositing for 15h, keeping the temperature for 2h, and cooling to room temperature. This step was repeated 2 times;
step 1.3, preparation of a ceramic matrix: placing the fiber preform with the deposited boron nitride interface layer in the step 1.2 and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, wherein the preparation process parameters of the silicon carbide ceramic matrix are as follows: and (3) heating the furnace body to 5000Pa, keeping the temperature for 1h, introducing mixed gas of trichloromethyl silane, hydrogen and argon, wherein the flow ratio of trichloromethyl silane to hydrogen to argon is 1: 5: 25, depositing for 30h, keeping the temperature for 2h, and cooling to room temperature. The step is repeatedly executed for 6 times to obtain the outer ring blank of the ceramic matrix composite turbine;
step 1.4, 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;
step 2.1, shallow hole processing: fixing the semi-finished product of the outer ring of the ceramic matrix composite turbine on a positioning tool, selecting a 45-degree diamond screwer with the thickness of 1mm, uniformly arranging the diamond screwer on the surface of the outer ring of the turbine in the weft direction according to the sequence of the spacing of 2.8mm between each row of holes, and arranging the diamond screwer in the warp direction according to the spacing of 2 degrees, wherein circular holes with the depth of 0.5mm and the diameter of 1.5mm are uniformly processed on the surface of the outer ring of the turbine in a certain arrangement sequence;
step 2.2, deposition by CVI: surface modified ceramic matrix compositesDepositing a SiC matrix on the outer ring matrix of the turbine to obtain the surface-treated matrix with the density of 2.5g/cm 3 The ceramic matrix composite turbine outer ring of (a);
step 3, preparation of abradable coating
Preparing an abradable coating on the surface-modified ceramic matrix composite turbine outer ring by a plasma spraying method, wherein an abradable coating system is BSAS and PHB. As shown in FIG. 2, it can be seen that the shallow holes are still clearly visible after the coating is prepared (note: the through holes in FIG. 2 are component film holes for cooling).
The bonding force between the outer ring of the ceramic matrix composite turbine and the abradable coating is detected through a universal material testing machine, and the bonding strength of the outer ring of the turbine is improved from 3.313MPa which is not subjected to surface treatment to 9.526MPa which is subjected to surface shallow hole machining. Therefore, by the surface treatment method of the ceramic matrix composite turbine outer ring, the binding force between the matrix and the abradable coating can be greatly improved, and the turbine outer ring with better mechanical property and oxidation resistance can be obtained.
Example 3
This example prepared a ceramic matrix composite turbine outer ring with an abradable coating by the following method:
step 1, preparing a ceramic matrix composite turbine outer ring semi-finished product;
step 1.1, preparing a fiber preform: in the embodiment, silicon carbide is used as a raw material, and a fiber preform is obtained by adopting a two-dimensional weaving method according to the structure, the shape and the size of the outer ring of the turbine;
step 1.2, preparing an interface layer: and (3) placing the graphite mold with the fiber preform in a boron nitride chemical vapor deposition furnace, and preparing a 120nm boron nitride interface layer on the surface of the fiber preform. The preparation process parameters of the boron nitride interface layer are as follows: and (3) heating the pressure in the furnace body to 800 ℃ at 850Pa, keeping the temperature for 2h, sequentially introducing argon, hydrogen, ammonia gas and boron trichloride gas, depositing for 35h, keeping the temperature for 2h, and cooling to room temperature. This step was repeated 2 times;
step 1.3, preparing a ceramic matrix: placing the fiber preform deposited with the boron nitride interface layer in the step 1.2 and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, wherein the preparation process parameters of the silicon carbide ceramic matrix are as follows: the pressure in the furnace body is 200Pa, the temperature is raised to 1000 ℃, the mixed gas of trichloromethyl silane, hydrogen and argon is introduced after the heat preservation is carried out for 1-2h, the flow ratio of trichloromethyl silane, hydrogen and argon is 1: 20: 10, the heat preservation is carried out for 2h after the deposition is carried out for 50h, and the temperature is reduced to the room temperature. The step is repeatedly executed for 6 times to obtain the outer ring blank of the ceramic matrix composite turbine;
step 1.4, 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;
step 2.1, shallow hole processing: fixing the semi-finished product of the ceramic matrix composite material turbine outer ring on a positioning tool, selecting a 45-degree diamond screwer with the thickness of 1mm, uniformly arranging the diamond screwer on the surface of the turbine outer ring in the weft direction according to the sequence of the spacing of 3.8mm between each row of holes, and arranging a certain arrangement sequence in the warp direction according to the spacing of 2 degrees to uniformly process round holes with the depth of 0.5mm and the diameter of 0.8mm on the surface of the turbine outer ring;
step 2.2, deposition of CVI: depositing a SiC matrix on the surface-treated ceramic matrix composite material turbine outer ring matrix to obtain the surface-treated ceramic matrix composite material turbine outer ring matrix with the density of 2.8g/cm 3 The ceramic matrix composite turbine outer ring of (a);
step 3, preparation of abradable coating
And preparing an abradable coating on the surface-treated ceramic matrix composite turbine outer ring by a plasma spraying method, wherein an abradable coating system is BSAS and PHB. As shown in FIG. 2, it can be seen that the shallow holes are still clearly visible after the coating is prepared (note: the through holes in FIG. 2 are component film holes for cooling).
The bonding force between the outer ring of the ceramic matrix composite turbine and the abradable coating is detected through a universal material testing machine, and the bonding strength of the outer ring of the turbine is improved from 3.313MPa which is not subjected to surface treatment to 9.529MPa which is subjected to surface shallow hole machining. Therefore, by the surface treatment method of the ceramic matrix composite turbine outer ring, the binding force between the matrix and the abradable coating can be greatly improved, and the turbine outer ring with better mechanical property and oxidation resistance can be obtained.
Comparative example 1
In the comparative example, the outer ring of the ceramic matrix composite turbine was prepared by the following method, and different from example 1, the parameters of the shallow hole were different:
step 1, preparing a semi-finished product of the ceramic matrix composite turbine outer ring;
step 1.1, preparing a fiber preform: according to the comparative example, the third-generation silicon carbide fiber is used as a raw material, and a fiber preform is obtained by adopting a two-dimensional weaving method according to the structure and the shape and the size of the outer ring of the turbine;
step 1.2, preparing an interface layer: and (3) placing the graphite mold clamped with the fiber preform in a boron nitride chemical vapor deposition furnace, and preparing a boron nitride interface layer on the surface of the fiber preform. The preparation process parameters of the boron nitride interface layer are as follows: and (3) heating the pressure in the furnace body to 700 Pa, keeping the temperature for 2h, sequentially introducing argon, hydrogen, ammonia gas and boron trichloride gas, depositing for 30h, keeping the temperature for 2h, and cooling to room temperature. This step was repeated 2 times;
step 1.3, preparation of a ceramic matrix: placing the fiber preform deposited with the boron nitride interface layer in the step 1.2 and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, wherein the preparation process parameters of the silicon carbide ceramic matrix are as follows: and (3) heating the pressure in the furnace body to 1200 ℃ at 350Pa, keeping the temperature for 1-2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon, wherein the flow ratio of trichloromethylsilane to hydrogen to argon is 1: 15: 20, depositing for 80h, keeping the temperature for 2h, and cooling to room temperature. The step is repeatedly executed for 6 times to obtain the outer ring blank of the ceramic matrix composite turbine;
step 1.4, 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;
Step 2.1, shallow hole processing: fixing the semi-finished product of the outer ring of the ceramic matrix composite turbine on a positioning tool, selecting a 45-degree diamond screwer with the thickness of 1mm, uniformly arranging the diamond screwer on the surface of the outer ring of the turbine in the latitudinal direction according to the sequence of the spacing of 4.5mm between each row of holes, and arranging the diamond screwer in the longitudinal direction according to the spacing of 4 degrees, wherein circular holes with the depth of 0.3mm and the diameter of 0.5mm are uniformly processed on the surface of the outer ring of the turbine in a certain arrangement sequence;
step 2.2, deposition by CVI: depositing a SiC matrix on the surface-treated ceramic matrix composite material turbine outer ring matrix to obtain the surface-treated ceramic matrix composite material turbine outer ring matrix with the density of 2.6g/cm 3 The ceramic matrix composite turbine outer ring of (a);
step 3, preparation of abradable coating
And preparing an abradable coating on the surface-treated ceramic matrix composite turbine outer ring by a plasma spraying method, wherein an abradable coating system is BSAS and PHB.
The bonding force between the outer ring of the ceramic matrix composite turbine and the abradable coating of the comparative example is detected through a universal material testing machine, and the bonding strength of the outer ring of the turbine is improved from 3.313MPa which is not subjected to surface treatment to 6.532MPa which is subjected to surface shallow hole machining. The bonding force strength is improved by a small amount relative to the above-described examples.
Comparative example 2
This comparative example differs from comparative example 1 in that: the various parameters of the shallow holes are different;
in the specific step 2.1, the processing process of the shallow hole is as follows: fixing the semi-finished product of the outer ring of the ceramic matrix composite turbine on a positioning tool, selecting a 45-degree diamond screwer with the thickness of 1mm, uniformly arranging the diamond screwer on the surface of the outer ring of the turbine in the weft direction according to the sequence of the spacing of 2.0mm between every two rows of holes, and arranging the diamond screwer in the warp direction according to the spacing of 2 degrees, wherein circular holes with the depth of 0.8mm and the diameter of 2.0mm are uniformly processed on the surface of the outer ring of the turbine in a certain arrangement sequence.
The bonding force between the outer ring of the ceramic matrix composite turbine and the abradable coating of the comparative example is detected through a universal material testing machine, and the bonding strength of the outer ring of the turbine is improved from 3.313MPa which is not subjected to surface treatment to 6.832MPa which is subjected to surface shallow hole machining. The amount of improvement in the bonding force strength is also small relative to the above examples.
Claims (8)
1. A method for preparing a ceramic matrix composite turbine outer ring with an abradable coating is characterized by comprising the following steps:
step 1, preparing a ceramic matrix composite turbine outer ring semi-finished product;
step 1.1, preparing a fiber preform: carbon fiber or silicon carbide fiber or the combination of the carbon fiber and the silicon carbide fiber is taken as a raw material, and a fiber preform is obtained by adopting a weaving method according to the structure and the shape and the size of the outer ring of the turbine;
step 1.2, preparing an interface layer: clamping the fiber preform by using a graphite mold, placing the fiber preform in a boron nitride chemical vapor deposition furnace, and preparing a boron nitride interface layer with a set thickness on the surface of the fiber preform;
step 1.3, preparation of a ceramic matrix: placing the fiber preform deposited with the boron nitride interface layer in the step 1.2 and a graphite mold into a silicon carbide chemical vapor deposition furnace together to prepare a silicon carbide ceramic matrix, so as to obtain a ceramic matrix composite material turbine outer ring blank;
step 1.4, 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;
step 2, surface modification of the ceramic matrix composite turbine outer ring semi-finished product;
step 2.1, shallow hole processing: fixing the ceramic matrix composite turbine outer ring semi-finished product on a positioning tool, and processing shallow holes with set depth on the surface of the ceramic matrix composite turbine outer ring semi-finished product according to a certain arrangement sequence;
the shallow holes are round holes with the depth equal to 0.5mm and the diameter equal to 0.8-1.5mm, the latitudinal direction is uniformly arranged on the surface of the outer ring of the turbine according to the sequence that the distance between every two rows of holes is 2.8mm-3.8mm, and the longitudinal direction is arranged according to the distance of 2 degrees;
step 2.2, deposition by CVI: depositing a SiC matrix on the ceramic matrix composite material turbine outer ring matrix treated in the step 2.1 to obtain a surface treated ceramic matrix composite material turbine outer ring;
step 3, preparing an abradable coating;
and preparing an abradable coating on the surface of the shallow hole machined in the outer ring of the ceramic matrix composite turbine.
2. The method for preparing a ceramic matrix composite turbine outer ring with an abradable coating of claim 1, wherein: in the step 1.2, the preparation process parameters of the boron nitride interface layer are as follows: the pressure in the furnace body is 40-850Pa, the temperature is raised to 700-1000 ℃, after heat preservation is carried out for 1-2h, argon, hydrogen, ammonia and boron trichloride are sequentially introduced, deposition is carried out for 15-35h, then heat preservation is carried out for 2h, and the temperature is reduced to room temperature.
3. The method for preparing a ceramic matrix composite turbine outer ring with an abradable coating of claim 2, wherein: the thickness of the boron nitride interface layer on the surface of the fiber preform is 120-650nm.
4. The method of preparing a ceramic matrix composite turbine outer ring with an abradable coating of claim 3, wherein: in the step 1.3, the preparation process parameters of the silicon carbide ceramic matrix are as follows: the pressure in the furnace body is 200-5000Pa, the temperature is raised to 950-1200 ℃, the temperature is kept for 1-2h, then mixed gas of trichloromethyl silane, hydrogen and argon is introduced, the flow ratio of trichloromethyl silane, hydrogen and argon is 1: 5-20: 10-25, the deposition is carried out for 30-80h, the temperature is kept for 2h, and the temperature is reduced to room temperature.
5. The method for preparing a ceramic matrix composite turbine outer ring with an abradable coating of claim 4, wherein: and 2.1, processing shallow holes on the surface of the ceramic matrix composite turbine outer ring semi-finished product by using a diamond drill.
6. The method of preparing a ceramic matrix composite turbine outer ring with an abradable coating of claim 5, wherein: in the step 3, BSAS and PHB are mixed according to a set volume ratio, and then the abradable coating is prepared by adopting a plasma spraying method; the abradable coating has a thickness in the range of 0.95mm to 1.5mm.
7. The method for preparing a ceramic matrix composite turbine outer ring with an abradable coating of claim 6, wherein: in the step 1.2, the preparation process parameters of the boron nitride interface layer are as follows: heating the furnace body to the pressure of 500Pa, keeping the temperature for 2h, sequentially introducing argon, hydrogen, ammonia and boron trichloride gas, depositing for 30h, keeping the temperature for 2h, and cooling to room temperature; in the step 1.3, the preparation process parameters of the silicon carbide ceramic matrix are as follows: heating the furnace body to the pressure of 350Pa, heating to 1200 ℃, keeping the temperature for 1-2h, introducing mixed gas of trichloromethylsilane, hydrogen and argon, depositing for 80h, keeping the temperature for 2h, and cooling to the room temperature; in the step 2.1, the shallow holes are round holes with the depth equal to 0.5mm and the diameter equal to 1.3mm, the latitudinal directions are uniformly arranged on the surface of the outer ring of the turbine according to the sequence of the spacing of 3.0mm between every two rows of holes, and the longitudinal directions are arranged at the spacing of 2 degrees.
8. An abradable coating ceramic matrix composite turbine outer ring prepared by the method of any one of claims 1-7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111592822.XA CN114315396B (en) | 2021-12-23 | 2021-12-23 | Ceramic matrix composite turbine outer ring with abradable coating and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111592822.XA CN114315396B (en) | 2021-12-23 | 2021-12-23 | Ceramic matrix composite turbine outer ring with abradable coating and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114315396A CN114315396A (en) | 2022-04-12 |
| CN114315396B true CN114315396B (en) | 2023-04-18 |
Family
ID=81054144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111592822.XA Active CN114315396B (en) | 2021-12-23 | 2021-12-23 | Ceramic matrix composite turbine outer ring with abradable coating and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114315396B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114850799B (en) * | 2022-05-23 | 2023-04-18 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite turbine outer ring machining tool and machining method |
| CN115139393A (en) * | 2022-06-21 | 2022-10-04 | 西安鑫垚陶瓷复合材料有限公司 | 2.5D turbine outer ring prefabricated part shaping mold and using method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090139808A1 (en) * | 2007-11-30 | 2009-06-04 | Messier Bugatti | Method of fabricating carbon fiber reinforced composite material parts |
| US20160229755A1 (en) * | 2013-09-20 | 2016-08-11 | General Electric Company | Ceramic matrix composites made by chemical vapor infiltration and methods of manufacture thereof |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6627019B2 (en) * | 2000-12-18 | 2003-09-30 | David C. Jarmon | Process for making ceramic matrix composite parts with cooling channels |
| US20120076927A1 (en) * | 2010-02-01 | 2012-03-29 | United States Government As Represented By The Secretary Of The Army | Method of improving the thermo-mechanical properties of fiber-reinforced silicon carbide matrix composites |
| CN105835455B (en) * | 2015-12-15 | 2019-05-10 | 西安鑫垚陶瓷复合材料有限公司 | Two-dimensional Carbon/silico-carbo SiClx composite material pin preparation method |
| CN108516852B (en) * | 2018-04-08 | 2020-06-26 | 中南大学 | Carbon-silicon carbide binary matrix carbon fiber composite material, and preparation method and application thereof |
| CN111039688A (en) * | 2019-12-25 | 2020-04-21 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of ceramic matrix composite material component with abradable coating and component |
| CN111018534A (en) * | 2019-12-25 | 2020-04-17 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of ceramic matrix composite material component with abradable coating and component |
| CN110981520A (en) * | 2019-12-25 | 2020-04-10 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of ceramic matrix composite material component with abradable coating and component |
| CN112759404B (en) * | 2021-01-27 | 2022-06-21 | 巩义市泛锐熠辉复合材料有限公司 | Preparation method of ceramic matrix composite internal thread |
-
2021
- 2021-12-23 CN CN202111592822.XA patent/CN114315396B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090139808A1 (en) * | 2007-11-30 | 2009-06-04 | Messier Bugatti | Method of fabricating carbon fiber reinforced composite material parts |
| US20160229755A1 (en) * | 2013-09-20 | 2016-08-11 | General Electric Company | Ceramic matrix composites made by chemical vapor infiltration and methods of manufacture thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114315396A (en) | 2022-04-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114315396B (en) | Ceramic matrix composite turbine outer ring with abradable coating and preparation method thereof | |
| CN114349525B (en) | Ceramic matrix composite turbine outer ring with abradable coating and preparation method thereof | |
| US10253639B2 (en) | Ceramic matrix composite gas turbine engine blade | |
| US7306826B2 (en) | Use of biased fabric to improve properties of SiC/SiC ceramic composites for turbine engine components | |
| JP6290224B2 (en) | Rotor-stator assembly for a gas turbine engine | |
| US6723382B2 (en) | Method for fabricating ceramic matrix composite | |
| CN104507677B (en) | Ceramic center body and manufacture method for airborne vehicle gas-turbine unit | |
| EP1826362B1 (en) | Manufacture of CMC articles having small complex features | |
| US7223465B2 (en) | SiC/SiC composites incorporating uncoated fibers to improve interlaminar strength | |
| US10465534B2 (en) | Machinable CMC insert | |
| EP1024121A2 (en) | Ceramic-based composite member and its manufacturing method | |
| US10458653B2 (en) | Machinable CMC insert | |
| CN111018534A (en) | Preparation method of ceramic matrix composite material component with abradable coating and component | |
| JP2006189031A (en) | Ceramic composite with integrated compliance/wear layer | |
| CN114014680A (en) | Ceramic matrix composite material turbine outer ring and preparation method thereof | |
| CN110981520A (en) | Preparation method of ceramic matrix composite material component with abradable coating and component | |
| CN111039688A (en) | Preparation method of ceramic matrix composite material component with abradable coating and component | |
| US11312664B2 (en) | Ceramic heat shields having a reaction coating | |
| CN113898417A (en) | Ceramic matrix composite turbine guide blade with turbulence structure and preparation method thereof | |
| CN112266257A (en) | Low-cost preparation method of reinforced silicon carbide composite material based on hybrid fiber between continuous C and SiC bundles and product thereof | |
| US11873571B2 (en) | Method for coating a component | |
| CN114057491B (en) | Preparation method of ceramic matrix composite material pulse detonation engine combustion chamber | |
| CN115093231A (en) | Ceramic matrix composite guide vane with tail edge cleft and preparation method thereof | |
| Halbig et al. | Diffusion Bonding and Brazing Approaches for Silicon Carbide Based Systems |
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 |
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 |
|
| CP03 | Change of name, title or address |