CN109437974B - C/SiC composite material with Mo-Si-B-O high-temperature oxidation-resistant coating and preparation method thereof - Google Patents

C/SiC composite material with Mo-Si-B-O high-temperature oxidation-resistant coating and preparation method thereof Download PDF

Info

Publication number
CN109437974B
CN109437974B CN201811381003.9A CN201811381003A CN109437974B CN 109437974 B CN109437974 B CN 109437974B CN 201811381003 A CN201811381003 A CN 201811381003A CN 109437974 B CN109437974 B CN 109437974B
Authority
CN
China
Prior art keywords
coating
composite material
sic
sic composite
matrix
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
Application number
CN201811381003.9A
Other languages
Chinese (zh)
Other versions
CN109437974A (en
Inventor
沙江波
李腾
温斯涵
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beihang University
Original Assignee
Beihang University
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Beihang University filed Critical Beihang University
Priority to CN201811381003.9A priority Critical patent/CN109437974B/en
Publication of CN109437974A publication Critical patent/CN109437974A/en
Application granted granted Critical
Publication of CN109437974B publication Critical patent/CN109437974B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
    • 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
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
    • C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
    • C04B41/5053—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials non-oxide ceramics
    • C04B41/5062—Borides, Nitrides or Silicides
    • C04B41/5071—Silicides
    • 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
    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
    • C04B41/81—Coating or impregnation
    • C04B41/85—Coating or impregnation with inorganic materials
    • C04B41/87—Ceramics

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Ceramic Products (AREA)

Abstract

The application discloses a C/SiC composite material with a Mo-Si-B-O high-temperature oxidation-resistant coating, which comprises a Mo-Si-B-O coating and a C/SiC matrix, wherein no mutual diffusion region exists between the Mo-Si-B-O coating and the C/SiC matrix, and the Mo-Si-B-O coating mainly comprises MoSi2MoB and SiO2Three-phase composition, the components of which are 73MoSi in phase volume ratio2：19MoB/Mo2B5：8SiO2Or 72MoSi2：22MoB/Mo2B5：6SiO2. The application also discloses a method for preparing the C/SiC composite material. The Mo-Si-B-O coating and the C/SiC matrix do not have an element interdiffusion zone, so that the stability of the structure of the coating during service is ensured, the service time of the coating is prolonged, and the high-temperature oxidation resistance of the C/SiC composite material is improved.

Description

C/SiC composite material with Mo-Si-B-O high-temperature oxidation-resistant coating and preparation method thereof
Technical Field
The application belongs to the field of composite material oxidation protection, relates to a C/SiC composite material with a Mo-Si-B-O high-temperature oxidation resistant coating and a preparation method thereof, and particularly relates to a method for preparing a Mo-Si-B-O composite coating on a carbon fiber reinforced ceramic matrix composite material by using a spark plasma sintering technology so as to improve the high-temperature oxidation resistance of the composite material.
Background
The Carbon Fiber Reinforced Ceramic Matrix Composite (CFRCMCs) have excellent characteristics of high specific strength, high specific modulus, corrosion resistance, high temperature resistance, low density and the like, particularly have good high-temperature mechanical property and thermal property, can keep the mechanical properties of strength, modulus and the like not to be reduced even when the temperature is over 2000 ℃ in an inert environment, and simultaneously have good fracture toughness and wear resistance, low linear expansion coefficient, high thermal conductivity, high gasification temperature and good thermal shock resistance, so that the Carbon Fiber Reinforced Ceramic Matrix Composite (CFRCMCs) are one of the most ideal thermal structural materials for improving the temperature of a combustion chamber of an engine or a heat engine and further improving the energy conversion rate in the research of new-generation engines and heat engines in developed countries.
However, carbon fiber reinforced ceramic matrix composites oxidize carbon fibers at temperatures above 400 ℃ in an oxidizing atmosphere, resulting in reduced material properties and failure of the material. In addition, many application environments of the carbon fiber reinforced ceramic matrix composite material have an oxidizing atmosphere, for example, in the service environment of an aeroengine, an oxidizing medium is easy to diffuse into the C/SiC composite material through microcracks and pores, the oxidation of the interface of carbon fibers and pyrolytic carbon is accelerated, and the service life of the material is shortened. Therefore, it is necessary to solve the problem of oxidation resistance of the carbon fiber reinforced ceramic matrix composite.
At present, the oxidation resistance research of the carbon fiber reinforced ceramic matrix composite material mainly focuses on two aspects: (1) the oxidation resistance of the material is enhanced by processing the matrix material; (2) the oxidation resistance of the material is enhanced by forming an integral oxidation resistant coating. Of these two treatments, the overall oxidation resistant coating is more effective. For example, the self-healing coating can form a continuous glass phase on the surface of the C/SiC composite material, seal cracks and pores in the coating or the matrix, isolate the contact between the matrix material and an oxidizing medium, and block the diffusion of oxygen, so that the service life of the C/SiC composite material on an aircraft engine can be effectively prolonged. The self-healing coating material below 1100 deg.C is boride, and B is generated by oxidation2O3A thin protective layer is formed on the surface, which is easy to flow into the micro-cracks in the matrix for sealing and blocking the oxygen diffusion. But above 1100 ℃, B2O3The vapor pressure of the self-healing coating is increased, the volatility is higher, and the oxidation resistance is reduced, so that the self-healing coating material with the temperature of more than 1100 ℃ is mainly silicon-based material.
Spark Plasma Sintering (SPS) is a new technique for rapid consolidation of powders. The SPS process has obvious advantages, has the distinct characteristics of high temperature rise speed, short sintering time, controllable organization structure, energy conservation, environmental protection and the like, can be used for preparing metal materials, ceramic materials and composite materials, and can also be used for preparing nano block materials, amorphous block materials, gradient materials and the like.
Disclosure of Invention
In order to solve the defects of the prior art, the invention selects the coating component of Mo-Si-B-O so as to take the oxidation performance of each temperature interval into consideration. The coating component of Mo-Si-B-O contains both Si source and B source, and has excellent oxidation resistance under high and low temperature conditions, so that the coating is selected as a coating for improving the oxidation resistance of the C/SiC composite material. Preparation of uniform on C/SiC composite material matrix by spark plasma sinteringA compact Mo-Si-B-O coating, a compact borosilicate (B) layer is formed on the surface of the Mo-Si-B coating after high-temperature oxidation2O3-SiO2) The oxide layer has self-healing capability due to the flowability, can well seal holes and cracks generated in the oxidation process, and can prevent oxygen from diffusing in a great degree, so that the high-temperature oxidation resistance of the coating is improved. Meanwhile, an element interdiffusion area cannot be generated between the coating and the substrate, so that the stability of the structure of the coating in a service period is effectively protected, and the service life of the coating is prolonged.
According to an aspect of the invention, a C/SiC composite material with a Mo-Si-B-O high-temperature oxidation resistant coating is provided, which comprises a Mo-Si-B-O coating and a C/SiC matrix, wherein no mutual diffusion region exists between the Mo-Si-B-O coating and the C/SiC matrix, and the Mo-Si-B-O coating mainly consists of MoSi2MoB and SiO2Three-phase composition, the components of which are 73MoSi in phase volume ratio2：19MoB/Mo2B5：8SiO2Or 72MoSi2：22MoB/Mo2B5：6SiO2。
According to another aspect of the invention, a method for preparing the C/SiC composite material with the Mo-Si-B-O high-temperature oxidation-resistant coating comprises the following steps:
(1) cutting the 2.5D woven C/SiC composite material by using a diamond wire cutting machine to prepare a C/SiC matrix;
(2) taking Mo- (20-40) Si- (18-25) B (at%) alloy elements as nominal chemical components as synthesis raw materials, and preparing a Mo-Si-B alloy sample by using non-consumable vacuum arc melting;
(3) carrying out mechanical impact crushing on the Mo-Si-B alloy sample prepared in the step (2), and then grinding the obtained powder to prepare Mo-Si-B alloy powder;
(4) and (2) sequentially putting the C/SiC matrix prepared in the step (1) and the Mo-Si-B alloy powder prepared in the step (3) into a graphite die, performing spark plasma sintering, wherein the sintering temperature is 1550-1700 ℃, the heating rate is 20-200 ℃/min, the pressure is 10-30 MPa, the heat preservation time is 1-6 min, and the Mo-Si-B alloy powder reacts with O in the SPS furnace and the C/SiC matrix to finally obtain the Mo-Si-B-O coating.
In some embodiments, in the step (3), the Mo-Si-B alloy powder may have a powder particle size distribution of 10 to 15 μm or 15 to 20 μm.
According to another aspect of the present invention, there is provided a C/SiC composite article protected by a Mo-Si-B-O coating consisting essentially of MoSi prepared according to the above method2MoB and SiO2Three phases.
According to another aspect of the invention, there is provided the use of a C/SiC composite material with a Mo-Si-B-O high temperature oxidation resistant coating according to claim 1 for new generation aircraft engine turbine blades, heat engine combustion chambers, rocket engine nozzles and the like.
The invention has the beneficial effects that:
1) the Mo-Si-B-O coating of the C/SiC composite material with the Mo-Si-B-O high-temperature oxidation-resistant coating prepared by the spark plasma sintering technology cannot generate a mutual diffusion region with a C/SiC matrix, is tightly combined, is not easy to peel off in the service process, prolongs the service life of the coating, and has strong practicability;
2) the Mo-Si-B-O coating prepared by the spark plasma sintering technology has high density, fine tissue and uniform phase distribution;
3) the Mo-Si-B-O coating prepared by the spark plasma sintering technology has short preparation period;
4) the Mo-Si-B-O coating prepared by the spark plasma sintering technology reduces the sintering time and the pressure intensity, has small damage to the C fiber of the matrix and ensures the mechanical property of the matrix to the maximum extent;
5) the Mo-Si-B-O coating prepared by the spark plasma sintering technology can control the phase composition and microstructure of the coating;
6) the method is simple and practical, so that the high-temperature oxidation resistance of the C/SiC composite material is greatly improved, and the method can be popularized to the field of other composite materials.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings used in the description of the embodiments will be briefly described below.
FIGS. 1(a) and (B) are XRD patterns of a C/SiC substrate and an XRD pattern of a prepared Mo-Si-B-O coating.
FIGS. 2(a) and (B) are scanning electron microscope images of Mo-Si-B-O coating cross-section obtained by spark plasma sintering of Mo-Si-B powder with particle size of 10-15 μm under different magnifications.
FIGS. 3(a) and (b) are photographs of the weight change curves of uncoated and coated C/SiC composites of the invention oxidized at 1300 ℃.
FIGS. 4(a) and (b) are sectional scanning electron microscope images of an uncoated C/SiC composite material and a coated C/SiC composite material of the present invention after oxidation at 1300 ℃ for 100 h.
FIGS. 5(a) and (B) are scanning electron microscope images of Mo-Si-B-O coating cross-section obtained by sintering Mo-Si-B powder with particle size of 15-20 μm by spark plasma sintering under different magnifications.
FIG. 6 is a scanning electron microscope image of a cross section of a Mo-62Si-5B coating of the comparative application after spark plasma sintering.
FIG. 7 is a scanning electron microscope image of a cross section of the Mo-52Si-15B coating of the comparative application after spark plasma sintering.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only illustrative and are not intended to limit the present application.
Example 1
1. Cutting the 2.5D woven C/SiC composite material by using a diamond wire cutting machine, cutting the composite material into cuboid samples with the length of 9mm, the width of 9mm and the height of 4mm to be used as C/SiC matrixes, and cleaning and then blowing the cuboid samples to be dry for later use;
2. taking Mo-40Si-18B (at%) alloy elements as nominal chemical components as synthetic raw materials, and preparing a Mo-Si-B alloy sample by utilizing non-consumable vacuum arc melting;
3. carrying out mechanical impact crushing on a Mo-Si-B alloy sample, and then grinding the powder to prepare Mo-Si-B alloy powder, wherein the particle size distribution of the Mo-Si-B alloy powder is 10-15 mu m;
4. sequentially placing the C/SiC matrix and the Mo-Si-B alloy powder in the steps into a graphite die with the diameter of 15mm, and sintering the Mo-Si-B alloy powder by using a discharge plasma sintering furnace to complete the densification process in a short time; and the discharge plasma sintering temperature is 1550 ℃, the heating rate is 60 ℃/min, the pressure is 25MPa, the heat preservation time is 3min, and the sample is cooled along with the furnace after sintering is finished, so that the Mo-Si-B-O coating is finally obtained.
Detecting the section of the Mo-Si-B-O coating prepared in the step 4 by using a scanning electron microscope, wherein the coating component is 73MoSi in terms of phase volume ratio2：19MoB/Mo2B5：8SiO2。
Cutting and processing the prepared C/SiC composite material sample with the Mo-Si-B-O coating, placing the sample into an alumina crucible, then placing the alumina crucible into a tube furnace to perform a static oxidation experiment at 1300 ℃, accurately measuring the sizes of all samples before the oxidation experiment, measuring the weight of the samples by using an electronic balance, and calculating the oxidation weight gain.
As can be seen from fig. 1(a), the C/SiC composite matrix mainly contains C fibers, SiC and a small amount of residual Si; as can be seen from FIG. 1(B), the Mo-Si-B-O coating structure prepared by spark plasma sintering is mainly composed of MoSi2、MoB/Mo2B5And SiO2And (4) forming. As can be seen from FIGS. 2(a) and (B), the Mo-Si-B-O coating is uniform and compact and has good combination with the C/SiC composite material matrix, the Mo-Si-B-O coating and the C/SiC composite material matrix do not generate interdiffusion zones, and the white color is Mo2B5MoB in pale white and MoSi in gray2SiO in a deep color2Phase, and the volume ratio of each phase is 73MoSi according to statistical data2：19MoB/Mo2B5：8SiO2。
As can be seen in FIG. 3(a), the weight change after 20h oxidation at 1300 ℃ for the C/SiC composite without the coating protection is about 9.6%, while as can be seen in FIG. 3(B), the weight change after 100h oxidation at 1300 ℃ for the C/SiC composite sample protected by the Mo-Si-B-O coating is only 0.25%. This shows that the high temperature oxidation resistance of the Mo-Si-B-O coating prepared on the C/SiC composite material by the spark plasma sintering technology is obviously improved.
As can be seen from FIG. 4(a), a layer of dense borosilicate (B) is formed on the surface of the Mo-Si-B-O coating after 100h of oxidation2O3-SiO2) The Mo-Si-B-O coating and the matrix are tightly combined in the oxidation process, no crack is generated, and a mutual diffusion region cannot be generated between the coating and the matrix, so that the stability of the coating in a service period is ensured, and the service life of the coating is prolonged.
Example 2
The method for improving the high-temperature oxidation resistance of the Mo-Si-B-O coating prepared on the C/SiC composite material substrate by utilizing the spark plasma sintering technology comprises the following steps:
1. cutting the 2.5D woven C/SiC composite material by using a diamond wire cutting machine, cutting the composite material into cuboid samples with the length of 9mm, the width of 9mm and the height of 4mm to be used as C/SiC matrixes, and cleaning and then blowing the cuboid samples to be dry for later use;
2. taking Mo-40Si-18B (at%) alloy elements as nominal chemical components as synthetic raw materials, and preparing a Mo-Si-B alloy sample by utilizing non-consumable vacuum arc melting;
3. carrying out mechanical impact crushing on a Mo-Si-B alloy sample, and then grinding the powder to prepare Mo-Si-B alloy powder, wherein the particle size distribution of the Mo-Si-B alloy powder is 15-20 mu m;
4. sequentially placing the C/SiC matrix sample and the Mo-Si-B alloy powder in the step into a graphite die with the diameter of 15mm, and sintering the Mo-Si-B alloy powder by using a discharge plasma sintering furnace to complete the densification process in a short time; the discharge plasma sintering temperature is 1600 ℃, the heating rate is 50 ℃/min, the pressure is 30MPa, the heat preservation time is 2min, and after sintering, the sample is cooled along with the furnace to finally obtain the Mo-Si-B-O coating;
detecting the cross section of the Mo-Si-B-O coating prepared in the step 4 by using a scanning electron microscope, wherein the coating component is 72MoSi in terms of phase volume ratio2：22MoB/Mo2B5：6SiO2；
Cutting and processing the prepared C/SiC composite material sample with the Mo-Si-B-O coating, placing the sample into an alumina crucible, then placing the alumina crucible into a tube furnace to perform a static oxidation experiment at 1300 ℃, accurately measuring the sizes of all samples before the oxidation experiment, measuring the weight of the samples by using an electronic balance, and calculating the oxidation weight gain.
As can be seen from FIGS. 5(a) and (B), the Mo-Si-B-O coating is uniform and dense and has good bonding with the substrate, and the white color is Mo2B5MoB in pale white and MoSi in gray2SiO in a deep color2Mutual diffusion regions are not generated between the phase, the coating and the substrate, and the volume ratio of each phase is 72MoSi according to statistical data2：22MoB/Mo2B5：6SiO2. Meanwhile, as can be seen from fig. 3(B), after the C/SiC composite material sample protected by the Mo-Si-B-O coating is oxidized for 100 hours at 1300 ℃, the weight change is only 0.29%, which indicates that the high-temperature oxidation resistance of the Mo-Si-B-O coating prepared on the C/SiC composite material by the spark plasma sintering technology is obviously improved.
Comparative example
Chinese patent application 201710984412.7 (hereinafter referred to as "comparative application") filed by the applicant discloses a method for preparing Mo-Si-B high temperature oxidation resistant coating on Nb-Si based alloy. Compared with the technical scheme of the comparison application, the technical improvement is as follows:
firstly, a matrix of a contrast application is Nb-Si-based high-temperature alloy and consists of intermetallic compounds and solid solutions of the alloy, while the matrix of the application is a C/SiC composite material reinforced by C fibers 2.5D, belonging to ceramic matrix composite materials, wherein the C fiber reinforced SiC composite material has good high-temperature mechanical properties and thermal properties, can still maintain the mechanical properties such as strength, modulus and the like at the temperature of more than 2000 ℃ in an inert environment, and has good fracture toughness and wear resistance, low linear expansion coefficient and good anti-seismic property.
Secondly, based on the C/SiC composite material matrix, the content of B is increased so as to accelerate the formation of a continuous and compact borosilicate oxide film with self-healing capability, and simultaneously, Mo-And the interdiffusion area generated by the interdiffusion phenomenon of elements cannot occur between the Si-B-O coating and the substrate. As shown in FIG. 5, no interdiffusion zone is generated between the coating and the substrate, and the obvious interface separation exists, so that the structural stability of the coating during service is effectively protected, and the service life of the coating is prolonged. Whereas the comparative application is based on a Nb-Si based superalloy substrate, with low B (as in fig. 6) and relatively high B (as in fig. 7) content, the interdiffusion is caused by the interdiffusion of elements between the coating and the substrate, in particular, a layer of Nb, Ti, Mo and Si interdiffusion between the substrate and the coating of the comparative application5Si3Interdiffusion layers, the interdiffusion of Si elements in coatings is known to reduce the service life of the coating. Therefore, the Mo-Si-B-O coating has longer service life under the condition of the same coating thickness.
Thirdly, according to the characteristics of the ceramic matrix composite, a diamond cutting machine is adopted when a sample is cut, meanwhile, in order to reduce the oxygen content in the sample, a method of mechanical impact and grinding is adopted when the powder is prepared, the particle size of the powder is increased, the oxygen content in the powder is reduced, the surface energy of the powder is reduced, and the oxygen content introduced into the C/SiC composite is limited within a certain range. Applicant's SiO in FIG. 5 of the present application and FIG. 6 of the comparative application2The amount of (A) is counted, and SiO of the application is found2The ratio is significantly lower than that of the comparative application, which is advantageous for ensuring the mechanical properties of the C fiber.
Fourthly, the strength of the C fiber can be damaged when the C/SiC composite material is in a high-pressure and high-temperature state for a long time, so that the mechanical property of the C/SiC composite material is kept to the maximum extent while the compactness of the Mo-Si-B-O coating is ensured, the sintering temperature is increased in the sintering process, and the pressure on a sample during sintering is reduced.
The above applications are only some embodiments of the present application. It will be apparent to those skilled in the art that various changes and modifications can be made without departing from the inventive concept herein, and it is intended to cover all such modifications and variations as fall within the scope of the invention.

Claims (4)

1. The C/SiC composite material with the Mo-Si-B-O high-temperature oxidation-resistant coating is characterized by comprising the Mo-Si-B-O coating and a C/SiC substrate, wherein the Mo-Si-B-O coating is prepared by using a plasma sintering technology, no mutual diffusion region exists between the Mo-Si-B-O coating and the C/SiC substrate, and the Mo-Si-B-O coating mainly comprises MoSi2MoB and SiO2Three-phase composition of MoSi2MoB and Mo2B5、SiO2Is 73: 19: 8 or 72: 22: 6.
2. a method for preparing the C/SiC composite material with the Mo-Si-B-O high temperature oxidation resistant coating of claim 1, comprising the steps of:
(1) cutting the 2.5D woven C/SiC composite material by using a diamond wire cutting machine to prepare a C/SiC matrix;
(2) taking Mo- (20-40) Si- (18-25) B (at%) alloy elements as nominal chemical components as synthesis raw materials, and preparing a Mo-Si-B alloy sample by using non-consumable vacuum arc melting;
(3) carrying out mechanical impact crushing on the Mo-Si-B alloy sample prepared in the step (2), and then grinding the obtained powder to prepare Mo-Si-B alloy powder;
(4) and (2) sequentially putting the C/SiC matrix prepared in the step (1) and the Mo-Si-B alloy powder prepared in the step (3) into a graphite die, performing spark plasma sintering, wherein the sintering temperature is 1550-1700 ℃, the heating rate is 20-200 ℃/min, the pressure is 10-30 MPa, the heat preservation time is 1-6 min, and the Mo-Si-B alloy powder reacts with O in the SPS furnace and the C/SiC matrix to finally obtain the Mo-Si-B-O coating.
3. The method according to claim 2, wherein in the step (3), the powder particle size distribution of the Mo-Si-B alloy powder is 10 to 15 μm or 15 to 20 μm.
4. Use of the C/SiC composite material according to claim 1 for new generation turbine blades for aeroengines, combustion chambers for heat engines, rocket engine nozzles.
CN201811381003.9A 2018-11-20 2018-11-20 C/SiC composite material with Mo-Si-B-O high-temperature oxidation-resistant coating and preparation method thereof Active CN109437974B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201811381003.9A CN109437974B (en) 2018-11-20 2018-11-20 C/SiC composite material with Mo-Si-B-O high-temperature oxidation-resistant coating and preparation method thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201811381003.9A CN109437974B (en) 2018-11-20 2018-11-20 C/SiC composite material with Mo-Si-B-O high-temperature oxidation-resistant coating and preparation method thereof

Publications (2)

Publication Number Publication Date
CN109437974A CN109437974A (en) 2019-03-08
CN109437974B true CN109437974B (en) 2020-12-08

Family

ID=65554548

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201811381003.9A Active CN109437974B (en) 2018-11-20 2018-11-20 C/SiC composite material with Mo-Si-B-O high-temperature oxidation-resistant coating and preparation method thereof

Country Status (1)

Country Link
CN (1) CN109437974B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110590373A (en) * 2019-10-28 2019-12-20 中原工学院 MoSi prepared by Flashing method2Method for preparing-MoB-SiC three-phase composite material

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104513068B (en) * 2013-10-08 2016-08-17 中国建筑材料科学研究总院 The anti-oxidation composite coating preparation technology of a kind of composition gradual change and application thereof
CN107790730B (en) * 2017-10-20 2023-07-28 北京航空航天大学 Method for preparing high-temperature oxidation-resistant coating on Nb-Si-based alloy
CN107904544A (en) * 2017-11-08 2018-04-13 宝鸡文理学院 A kind of preparation method of refractory metal surfaces antioxidant coating

Also Published As

Publication number Publication date
CN109437974A (en) 2019-03-08

Similar Documents

Publication Publication Date Title
Jin et al. Advances in oxidation and ablation resistance of high and ultra-high temperature ceramics modified or coated carbon/carbon composites
CN106435443B (en) A kind of preparation method of Environmental Barrier Coatings on Si-based Ceramics
Feng et al. Ablation behavior of single and alternate multilayered ZrC-SiC coatings under oxyacetylene torch
US6322897B1 (en) Metal-ceramic gradient material, product made from a metal-ceramic gradient material and process for producing a metal-ceramic gradient material
JP6002769B2 (en) Super heat resistant material stable in wet environment and method for producing the same
Chen et al. Microstructure and anti-oxidation properties of Yb2Si2O7/SiC bilayer coating for C/SiC composites
CN104529498A (en) One-step preparation method of multi-layer environmental barrier coatings through spark plasma sintering (SPS)
CN108517518B (en) Preparation method of composite coating for improving high-temperature oxidation resistance of titanium alloy
JPH07157384A (en) Heat and oxidation resistant high strength member and production thereof
CN108585897A (en) A kind of refractory metal high-temperature oxidation resistant Si-Mo-YSZ coatings and preparation method thereof
Hu et al. Influence of oxidation behavior of feedstock on microstructure and ablation resistance of plasma-sprayed zirconium carbide coating
CN113151772A (en) Novel high-temperature corrosion-resistant thermal barrier coating with double ceramic layer structure and preparation method thereof
Liu et al. Impact of introducing SiC and Si on microstructure and oxidation resistance of MoSi2/SiC coated C/C composites prepared by SAPS
CN109437974B (en) C/SiC composite material with Mo-Si-B-O high-temperature oxidation-resistant coating and preparation method thereof
Zamharir et al. Challenges toward applying UHTC-based composite coating on graphite substrate by spark plasma sintering
JP2019507828A (en) Adhesion promoting layer for bonding a high temperature protective layer on a substrate and method for producing the same
Ren et al. Preparation of MoSi2-modified HfB2-SiC ultra high temperature ceramic anti-oxidation coatings by liquid phase sintering
CN108504980B (en) High-temperature-resistant ablation-resistant composite coating and preparation method thereof
JP4690709B2 (en) Heat resistant material and manufacturing method thereof
Ma et al. Ablation behavior of Zr–Al (Si)–C layered carbides modified 3D needled C/SiC composites
Liu et al. Ablation resistance and mechanism of SiC/ZrC-ZrB2 double layer coating for C/C composites under plasma flame
CN112063966B (en) Method for improving high-temperature ablation resistance of molybdenum alloy surface
CN115259903A (en) High-precision high-temperature ablation-resistant coating formed on base material, preparation method thereof and composite material containing coating
JPH0598414A (en) Ceramic coated carbon fiber-reinforced carbon composite material for ground apparatus and production thereof
CN114315390A (en) Carbon/carbon composite material surface wide-temperature-range long-life antioxidant coating and low-temperature preparation method

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