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A kind of preparation method of continuous oxide fiber fabric surface coating

A surface coating and fiber fabric technology, applied in the field of preparation of continuous oxide fiber fabric surface coating, can solve the problem that the interface between pyrolytic carbon and BN cannot meet the requirements of anti-oxidation, long life and high reliability, and harsh service conditions, etc. problems, to achieve the effect of short preparation cycle, low equipment requirements, and improved strength and toughness

Active Publication Date: 2021-02-09
AVIC BEIJING AERONAUTICAL MFG TECH RES INST +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, the interface layer of fiber reinforced ceramic matrix composites mainly includes pyrolytic carbon interface layer and BN interface layer, but the interface layer of pyrolytic carbon and BN is mainly for non-oxide continuous fiber reinforced ceramic matrix composites, because oxide fiber reinforced oxide ceramics Matrix composite materials are mainly used in oxygen and gas environments, and the service conditions are relatively harsh. The interface between pyrolytic carbon and BN cannot meet the requirements of oxidation resistance, long life and high reliability in service environments.

Method used

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  • A kind of preparation method of continuous oxide fiber fabric surface coating

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preparation example Construction

[0027] (12) Preparation of coating phase precursor

[0028] Prepare the coating precursor solution by stirring and mixing the solution. The precursor solution is one or more of the following mixed solutions, nitrate and phytic acid mixed solution, nitrate and phosphoric acid, citric acid mixed solution, nitrate and phosphoric acid Ammonium dihydrogen mixed solution, the concentration of nitrate in the coating precursor solution is 30-80%;

[0029] (13) Continuous oxide fiber preform impregnation process

[0030] Immerse the pretreated continuous oxide fiber preform in the above precursor solution for 10-20s, take it out, put it in deionized water at 50-100°C, and keep stirring for 5-15min, rinse the fiber cloth with deionized water after taking it out surface to remove ions in solution and loose solids on the surface;

[0031] (14) Coating drying and heat treatment process

[0032] The fiber preform impregnated with the precursor solution is put into an oven to dry, and the...

Embodiment 1

[0036] Put the 610 alumina fiber fabric of 3M company in a muffle furnace for heat treatment at 800°C for 1 hour, and remove the surface sizing agent before use.

[0037] Stir and mix lanthanum nitrate (La(NO3)3·6H2O) and phytic acid (pc) in a deionized medium to prepare a precursor solution, wherein the concentration of lanthanum nitrate is 50%. Then, immerse the alumina fiber fabric in the precursor solution for 15 seconds, take it out, put it in deionized water at 90°C, and keep stirring for 5 minutes, so that LaPO4 is deposited on the surface of the fiber cloth, and rinse the coating with deionized water after taking it out. 20s on the surface of the fiber cloth to remove ions in the solution and loose solids on the surface. Then arrange the fibers in an oven and dry at 120°C for 15 minutes, then put them into a muffle furnace, heat-treat at 800°C for 5 minutes, and then take them out directly, so that the impregnation-heat treatment cycle is repeated 6 times, and finally ...

Embodiment 2

[0039] After soaking the mullite fiber fabric produced by Mitsubishi Corporation in acetone for 30 minutes, place it in a muffle furnace for heat treatment at 500°C for 2 hours, remove the surface sizing agent, and set it aside for use.

[0040] The precursor solution was prepared by magnetic stirring and mixing neodymium nitrate (Nd(NO3)3·6H2O) and ammonium dihydrogen phosphate (ADPH) in a deionization medium, wherein the concentration of lanthanum nitrate was 60%. Then, immerse the alumina fiber fabric in the precursor solution for 10 seconds, take it out, put it in deionized water at 80°C, and keep stirring for 8 minutes, so that NdPO4 is deposited on the surface of the fiber cloth, and rinse the coated surface with deionized water after taking it out. 15s on the surface of the fiber cloth to remove ions in the solution and loose solids on the surface. Then arrange the fibers in an oven and dry at 100°C for 20 minutes, then put them into a muffle furnace, heat-treat at 900°...

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Abstract

The invention belongs to the preparation technology of continuous fiber-reinforced ceramic matrix composite material, and relates to a method for preparing the coating interface between fiber and matrix in continuous oxide fiber reinforced oxide ceramic matrix composite material. The invention first prepares the coating phase phosphate precursor solution, then dips the oxide fiber preform into the precursor solution, takes it out after the impregnation is completed, performs desizing treatment at an appropriate temperature, and obtains the fiber surface through repeated dipping-heat treatment processes phosphate coating. The coating can not only protect the fibers from mechanical and thermal damage during the densification process of the matrix, but also provide a suitable weak interface bonding for the fibers and the matrix, thereby improving the strength and toughness of the material. In addition, the phosphate coating has the characteristics of high temperature oxidation resistance, which can greatly improve the service life and high temperature reliability of the composite material.

Description

technical field [0001] The invention belongs to the preparation technology of continuous fiber reinforced ceramic matrix composite material, and relates to a preparation method of continuous oxide fiber fabric surface coating. Background technique [0002] Continuous fiber-reinforced composite materials have the characteristics of low density, high specific strength, high specific modulus, high temperature resistance, oxidation resistance, and good reliability. They are the development direction of high-performance aero-engine materials. Among them, ceramic matrix composite (CMC) is a structural material with high temperature (1650°C) and low density (2.5g / cm3~3.3g / cm3), which is expected to replace nickel with a density greater than 8.0g / cm3 The base or single crystal nickel alloy is used as the engine's combustion chamber, flame stabilizer, inner cone, tail nozzle, worm wheel outer ring, high-pressure turbine, low-pressure turbine and other components. Compared with the S...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/447
Inventor 梁艳媛焦健王岭杨金华刘善华张冰玉
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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