Self-healing ceramic matrix composite combustion chamber flame tube and its preparation method and application

A composite material and combustion chamber technology, which can be used in combustion methods, combustion chambers, combustion equipment, etc., can solve problems such as restricting the application of SiC ceramic matrix composite materials, damage to the interface phase and fiber oxidation, accelerated material damage and corrosion, etc. Good mechanical properties, high degree of densification, strong anti-oxidation effect

Active Publication Date: 2018-02-23
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0004] The existing silicon carbide ceramic matrix composites have excellent performance and are candidates to replace superalloys as materials for the hot end components of aero-engines. However, in high-temperature oxidizing environments, SiC f The micro-cracks and pores generated in composite materials are easy to become oxidizing medium (O 2 and H 2 O) and gas corrosion channels, resulting in the oxidation damage of the interface phase and fibers in the SiC component; in addition, the stress in the service environment will promote the cracking of the composite material matrix, accelerate the damage and corrosion of the material, and affect its high temperature gas environment. The requirement of long service life under the lower service conditions seriously restricts the application of SiC ceramic matrix composites in the engine combustion chamber flame tube

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  • Self-healing ceramic matrix composite combustion chamber flame tube and its preparation method and application

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preparation example Construction

[0028] The invention provides a method for preparing a composite material combustion chamber flame tube, comprising the following steps:

[0029] S1: The SiC interface was prepared by the chemical vapor deposition method on the prefabricated body of the combustor flame tube; the reaction gas of the chemical vapor deposition method was trichloromethylsilane; Braided, wherein, the braiding angle is 20-45°, the volume fraction of silicon carbide fiber is 30%-50%; the chemical vapor deposition method is specifically: trichloromethylsilane as the reaction gas, hydrogen as the carrier gas, argon gas It is a diluent gas, the deposition temperature is 1100-1230°C, the pressure is 1-5kPa, and the deposition time is 5-15h; wherein, the volume ratio of hydrogen to trichloromethylsilane is 1:8-1:12.

[0030] S2: Using the mixed solution of polycarbosilane and xylene as the precursor solution, the product obtained in step S1 is densified by the precursor impregnation and cracking method; t...

Embodiment 1

[0036] The silicon carbide fiber is woven into the combustor flame tube preform by three-dimensional four-step method, wherein the weaving angle is 40°, and the volume fraction of silicon carbide fiber is 35%; the obtained combustor flame tube preform is prepared by chemical vapor deposition method. interface, in which trichloromethylsilane is used as the reaction gas, hydrogen is used as the carrier gas, argon is used as the diluent gas, the volume ratio of hydrogen to trichloromethylsilane is 1:10, the deposition temperature is 1130°C, and the pressure is 4.5kPa. The deposition time was 8 hours, and the thickness of the prepared SiC interface was 6 μm.

[0037] The product obtained above was impregnated with a mixed solution of polycarbosilane and xylene under vacuum conditions for 6 hours, and then dried at 120°C; the dried product was cracked at 1000°C in nitrogen for 4 hours; the precursor impregnation cracking method was repeated for 10 cycles , the obtained silicon carb...

Embodiment 2

[0040] The silicon carbide fiber is woven into the combustor flame tube preform by three-dimensional four-step method, wherein the weaving angle is 30°, and the volume fraction of silicon carbide fiber is 35%; the obtained combustor flame tube preform is prepared by chemical vapor deposition method. interface, in which trichloromethylsilane is used as the reaction gas, hydrogen is used as the carrier gas, and argon is used as the diluent gas. The volume ratio of hydrogen to trichloromethylsilane is 1:9, the deposition temperature is 1150°C, and the pressure is 3kPa. The time is 6 hours, and the thickness of the prepared SiC interface is 4 μm.

[0041] The product obtained above was impregnated with a mixed solution of polycarbosilane and xylene under vacuum conditions for 5 hours, and then dried at 120°C; the dried product was cracked at 950°C in nitrogen for 6 hours; the precursor dipping cracking method was repeated for 8 cycles , the obtained silicon carbide matrix has a de...

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Abstract

The invention relates to a self-healing ceramic matrix composite combustor liner, a preparation method and application thereof. The preparation method includes the steps of: employing chemical vapor deposition to prepare an SiC interface with a combustor liner perform; then performing densification by precursor infiltration pyrolysis; repeating precursor infiltration pyrolysis until the density of the obtained silicon carbide substrate is 1.6-1.8g / cm<3>; preparing a SiC matrix layer and a BCx matrix layer on the surface of the silicon carbide substrate by chemical vapor infiltration to obtain a carbon boron silicon self-healing substrate with a density of 2.0-2.5g / cm<3>, and then carrying out modification treatment at 1000DEG C for 1-3h, thus obtaining the composite combustor liner. The composite combustor liner provided by the invention can improve the bending strength, high temperature resistance, oxidation resistance, self-healing properties and gas combustion efficiency of the combustor liner, and reduce the combustor liner mass and waste emission.

Description

technical field [0001] The invention relates to the technical field of structural materials for aviation, in particular to a self-healing ceramic matrix composite material combustion chamber flame tube and its preparation method and application. Background technique [0002] The combustion chamber is one of the core components of an aero-engine. Its main function is to convert the chemical energy of the fuel into heat energy through combustion, so as to improve the ability of the gas to expand in the turbine and nozzle. In the structural composition of the combustion chamber, the flame tube is the place to organize the combustion, and it is the key component to ensure the air splitting, sufficient combustion, uniform mixing and effective cooling of the wall. The reliability, economy and life of the combustor depend largely on the reliability and effectiveness of the flame tube, so the development of a high-performance and long-life combustor flame tube plays a vital role in ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/66C04B35/80C04B35/565C04B41/89F23R3/42
CPCC04B35/565C04B35/571C04B35/66C04B35/806C04B41/009C04B41/52C04B41/89C04B2235/483C04B2235/77C04B2235/96C04B2235/9607F23R3/42C04B41/5059C04B41/5058C04B41/5031
Inventor 罗瑞盈王天颖
Owner BEIHANG UNIV
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