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Multilayer ceramic-based composite material for aero-engine thermal structural member and preparation method thereof

An aero-engine, multilayer ceramic technology, applied in the field of materials, can solve the problems of erosion, performance attenuation, mechanical property damage of composite materials, etc., and achieve the effect of reducing porosity, improving mechanical behavior, and improving mechanical properties

Active Publication Date: 2021-12-03
湖北瑞宇空天高新技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In the current process of preparing ceramic matrix composites, due to the defects of the preparation process, there will be inherent pores inside and outside the composite material, and these inherent pores will become the source of crack induction and cause damage to the mechanical properties of the composite material. In addition, these The existence of inherent pores will cause the interior of ceramic matrix composites to be eroded by oxygen in a high-temperature aerobic environment, which will cause performance attenuation

Method used

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  • Multilayer ceramic-based composite material for aero-engine thermal structural member and preparation method thereof

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preparation example Construction

[0043] The invention provides a method for preparing a multilayer ceramic matrix composite material for thermal structural parts of an aero-engine, comprising the following steps:

[0044] Step 1: Using continuous fibers as the toughening phase to prepare a fiber preform, the structure of the preform is any one of ply stitching, three-dimensional braided structure, 2.5D and other structures, the continuous fiber is silicon carbide fiber, and the The fiber volume fraction in the preform is 30-45%; step 2: use chemical vapor deposition to deposit on the surface of the fiber in the fiber preform to obtain a composite interface of pyrolytic carbon and SiC nanowires to obtain a primary body; step 3: use vacuum - Pressurized impregnation process to quickly densify the product obtained in step 2 to obtain a secondary green body; step 4: use chemical vapor infiltration process to fill the secondary green body with matrix, and perform pre-oxidation to obtain a third-grade green body; st...

Embodiment 1

[0051] The invention provides a method for preparing a multilayer ceramic matrix composite material for thermal structural parts of an aero-engine, comprising the following steps:

[0052] Step 1: using continuous fibers as the toughening phase to prepare a fiber preform, the structure of the preform is ply stitching, the continuous fibers are silicon carbide fibers, and the fiber volume fraction in the preform is 45%;

[0053] Step 2: Deposit the surface of the fiber in the fiber preform by chemical vapor deposition to obtain a composite interface of pyrolytic carbon and SiC nanowires to obtain a primary green body; the preparation method of the pyrolytic carbon interface is to place the preform in pyrolysis In the carbon deposition equipment, propane is used as the deposition gas, nitrogen is used as the dilution gas, the deposition temperature is 700°C, the deposition time is 5h, and the deposition pressure is 1200Pa, wherein the propane flow rate is 50g / h, and the nitrogen ...

Embodiment 2

[0060] The invention provides a method for preparing a multilayer ceramic matrix composite material for thermal structural parts of an aero-engine, comprising the following steps:

[0061] Step 1: using continuous fibers as the toughening phase to prepare a fiber preform, the preform structure is a three-dimensional braided structure, the continuous fibers are silicon carbide fibers, and the fiber volume fraction in the preform is 40%;

[0062] Step 2: Deposit the surface of the fiber in the fiber preform by chemical vapor deposition to obtain a composite interface of pyrolytic carbon and SiC nanowires to obtain a primary green body; the preparation method of the pyrolytic carbon interface is to place the preform in pyrolysis In the carbon deposition equipment, propane is used as the deposition gas, nitrogen is used as the dilution gas, the deposition temperature is 800 ° C, the deposition time is 3.5 h, and the deposition pressure is 1200 Pa, wherein the propane flow rate is 8...

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Abstract

The invention discloses a multilayer ceramic-based composite material for an aero-engine thermal structural member and a preparation method of the multilayer ceramic-based composite material. The preparation method comprises the following steps: preparing a fiber preform from continuous fibers; preparing a pyrolytic carbon and SiC nanowire composite interface phase on the internal fiber surface of the preform, densifying the preform with the composite interface phase by adopting a vacuum-pressure impregnation process to obtain a second-stage green body, performing matrix filling on the second-stage green body by adopting a chemical vapor infiltration process, and performing pre-oxidation to obtain a third-stage green body; introducing a pyrolytic carbon layer into the third-stage green body through a chemical vapor infiltration process, introducing carbon nanowires through a catalyst-assisted deposition method to obtain a fourth-stage green body, finally, preparing a SiC hole sealing coating on the surface of the fourth-stage green body through a melt siliconizing method, wherein the prepared ceramic-based composite material is low in porosity, has the ablation-resistant and corrosion-resistant characteristics, and excellent mechanical property can still be kept under the high-temperature aerobic condition.

Description

technical field [0001] The invention relates to the field of materials, in particular to a multilayer ceramic matrix composite material for thermal structural parts of an aero-engine and a preparation method thereof. Background technique [0002] The materials used in the thermal structural parts of aero-engines need to meet the requirements of high temperature resistance, high strength, and high reliability. With the increase of the inlet temperature of the aero-engine turbine, traditional high-temperature alloy materials are difficult to meet the working requirements of the engine. In addition, the traditional high-temperature alloy materials The high density further limits the improvement of the thrust-to-weight ratio of aero-engines. Compared with traditional superalloy materials, ceramic matrix composite materials have excellent properties such as low density, high strength, high temperature resistance, oxidation resistance, and corrosion resistance. Using them to repla...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/52C04B35/622
CPCC04B35/80C04B35/52C04B35/622C04B2235/5244C04B2235/6562C04B2235/6567C04B2235/77C04B2235/96
Inventor 罗瑞盈崔光远
Owner 湖北瑞宇空天高新技术有限公司
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