Preparation method of novel high temperature anti-oxidation C/C composite coating
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A high-temperature anti-oxidation, composite material technology, applied in the field of composite materials, can solve the problems of gaps and holes, insufficient anti-oxidation ability, etc., and achieve the effects of long service life, excellent anti-oxidation, and simple process
Inactive Publication Date: 2017-11-24
SUZHOU HONGJIU AVIATION THERMAL MATERIALS TECH CO LTD
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The surface density of the prepared material is greatly improved, and the oxidation resistance is improved, but gaps and holes will appear at high temperatures
[0006] There are many carbon/carbon composite coatings currently on the market, but considering the insufficient oxidation resistance of the existing carbon/carbon composite coatings, as well as
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Embodiment 1
[0022] The C / C composite material is used as the matrix, the metal W is used as the transition layer, and the platinum group metal Ir is used as the coating, and the three layers of materials are sequentially compounded; the total thickness of the C / C composite material is 3mm~6mm, and the composite material The carbon fibers in the coating are distributed laterally, the thickness of the coating is 8 μm to 20 μm, and the average grain size of the coating is 1 μm to 2 μm.
[0023] The total thickness of the C / C composite material is 3mm~6mm, and the density is 1.2~1.6g / cm 3 , and the spacing between carbon fibers shall not be greater than 20 μm, and they are distributed laterally.
[0024] Platinum group metal Ir is used for the coating, the thickness of the coating is 8μm~20μm, and the average grain size of the coating is 1μm~2μm, and the Ir coating is deposited on the surface of the transition layer by using a double glow plasma surface alloying furnace.
[0025] Its prepara...
Embodiment 2
[0030] The C / C composite material is used as the matrix, the metal W is used as the transition layer, and the platinum group metal Ir is used as the coating, and the three layers of materials are sequentially compounded; the total thickness of the C / C composite material is 3mm~6mm, and the composite material The carbon fibers in the coating are distributed laterally, the thickness of the coating is 8 μm to 20 μm, and the average grain size of the coating is 1 μm to 2 μm.
[0031] The total thickness of the C / C composite material is 3mm~6mm, and the density is 1.2~1.6g / cm 3 , and the spacing between carbon fibers shall not be greater than 20 μm, and they are distributed laterally.
[0032] Platinum group metal Ir is used for the coating, the thickness of the coating is 8μm~20μm, and the average grain size of the coating is 1μm~2μm, and the Ir coating is deposited on the surface of the transition layer by using a double glow plasma surface alloying furnace.
[0033] A method fo...
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Abstract
The invention relates to a preparation method of a novel high temperature anti-oxidation C/C composite coating. A C/C composite material is adopted as the substrate, metal W is taken as the transition layer, platinum group metal Ir is employed as the coating, and the three layers of materials are compounded in order to obtain the composite coating. The C/C composite material has carbon fiber in transverse distribution and a density of 1.2-1.6g/cm, and is an ideal ultrahigh temperature thermal structure material in the aerospace field. The coating adopts the platinum group metal Ir with a thickness of 8microm-20microm, wherein the average crystal grain size of the coating is 1microm-2microm, and a double glow plasma surface alloying furnace is employed to deposit the Ir coating on the transition layer surface, Ir has a series of advantages of high strength, high melting point, good chemical stability, excellent oxidation resistance, no reaction with C at a temperature lower than 2280DEG C, and effective obstruction of C diffusion, etc. The invention brings the advantages of the composite structure and the excellent properties of all materials into play to make up for the shortcomings of insufficient oxidation under high temperature, high making cost and the like of the C/C composite coating, and realizes long-term, safe and stable work of the C/C composite material in a high temperature environment.
Description
technical field [0001] The invention belongs to the technical field of composite materials, and in particular relates to a preparation method of a novel high-temperature oxidation-resistant C / C composite coating. Background technique [0002] C / C composite material is an ideal ultra-high temperature thermal structural material in the aerospace field. It has low density, high specific strength, high specific modulus, low thermal expansion coefficient, thermal shock resistance, creep resistance, ablation resistance, wear resistance, etc. The series of excellent properties, especially at 1000°C to 2300°C, the strength increases with the increase of temperature, and has been widely used in hypersonic aircraft nose cones, solid rocket motor nozzles and throat linings, aircraft brake discs, etc. [0003] However, C / C composites will start to oxidize at 370°C in the air, which will reduce the physical and mechanical properties of the composites and cause serious damage to the mater...
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