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Continuous fiber reinforced ceramic matrix composite material flame stabilizer and its preparation method and application

A flame stabilizer and composite material technology, which is applied in combustion methods, continuous combustion chambers, combustion equipment, etc., can solve the problems of burning engine parts, increasing engine load, and destroying engines, and achieves increasing engine thrust, reducing component weight, and reducing quality effect

Active Publication Date: 2018-02-23
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Most of the existing afterburner components are made of metal materials such as titanium and nickel alloys, which are heavy and not resistant to high temperatures. Additional air cooling devices are required to increase the load of the engine, and alloys may cause fire risks under high-temperature and high-speed flame friction. The flame can spread rapidly and continue to burn, causing the engine parts to be burned, resulting in serious damage to the engine. Therefore, the development of new high-temperature-resistant high-performance composite materials for the hot-end parts of aero-engines has become an inevitable development trend in the current manufacturing of military aero-engines

Method used

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  • Continuous fiber reinforced ceramic matrix composite material flame stabilizer and its preparation method and application
  • Continuous fiber reinforced ceramic matrix composite material flame stabilizer and its preparation method and application

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preparation example Construction

[0022] The invention provides a kind of preparation method of composite material flame stabilizer, comprises the following steps:

[0023] S1: The flame stabilizer prefabricated body is prepared by using continuous SiC fiber in three-dimensional four-way weaving method. In the flame stabilizer prefabricated body, the volume fraction of continuous SiC fiber is 51.2% to 54.6%. The flame stabilizer prefabricated body is shaped according to the design and size processing, the overall size retains a reprocessing allowance of 0.1 to 0.5mm; the surface of the processed flame stabilizer preform is prepared by chemical vapor deposition (C-SiC) n Composite material interface phase, n=1~5, that is, the C interface layer and the SiC interface layer are prepared alternately in sequence, and the C interface layer is in contact with the surface of the flame stabilizer preform; (C-SiC) nThe interfacial phase of the composite material includes a C interface layer and a SiC interface layer: the...

Embodiment 1

[0029] Design the structure and size of the continuous fiber-reinforced ceramic matrix composite flame stabilizer preform according to the working requirements of the engine afterburner; put the continuous SiC fiber into the high-temperature graphite furnace, vacuumize, raise the temperature to 800°C, keep the temperature for 1 hour, and then according to The structure and design dimensions of the flame stabilizer and the prefabricated body of the flame stabilizer were prepared by using the three-dimensional four-way weaving method; the corresponding graphite mold was designed according to the size requirements, and holes were processed on the graphite mold, and the prepared flame stabilizer prefabricated body was put into In the graphite mould, adjust the position and shape of the flame stabilizer preform in the mould, so that the preform is evenly distributed in the mould, close to the actual shape and size, and retain a reprocessing allowance of 0.1mm, combine and fix the mou...

Embodiment 2

[0034] Design the structure and size of the continuous fiber-reinforced ceramic matrix composite flame stabilizer preform according to the working requirements of the engine afterburner; put the continuous SiC fiber into the high-temperature graphite furnace, vacuumize, raise the temperature to 800°C, keep the temperature for 1 hour, and then according to The structure and design dimensions of the flame stabilizer and the prefabricated body of the flame stabilizer were prepared by using the three-dimensional four-way weaving method; the corresponding graphite mold was designed according to the size requirements, and holes were processed on the graphite mold, and the prepared flame stabilizer prefabricated body was put into In the graphite mold, adjust the position and shape of the preform of the flame stabilizer in the mold, so that the preform is distributed in the mold evenly and close to the actual shape and size, and a reprocessing allowance of 0.1mm is reserved, and the mol...

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Abstract

The present invention relates to a continuous fiber reinforced ceramic base composite material flame stabilizer and a preparation method and application thereof. The preparation method is as follows: preparing a (C-SiC) n composite material interphase on the surface of a flame stabilizer preform by a chemical vapor deposition method, wherein the flame stabilizer preform is prepared from SiC fiber; then using a chemical vapor infiltration method for densification to obtain a densified flame stabilizer; and machining the densified flame stabilizer into a final design size to obtain the composite material flame stabilizer. The composite material flame stabilizer can reduce the mass of an engine, improve the working efficiency of the flame stabilizer, increase engine thrust and eliminate fire risks due to high-speed friction of flame so as to meet requirements of development of a new generation of aircraft engines.

Description

technical field [0001] The invention relates to the technical field of aircraft engine structural materials, in particular to a continuous fiber reinforced ceramic matrix composite material flame stabilizer and its preparation method and application. Background technique [0002] In modern advanced military aviation aircraft (such as turbojet, turbofan, etc.), the afterburner is an indispensable afterburner in the engine. If military aviation aircraft want to improve flexibility, maintain sufficient lift and achieve supersonic cruise, it is necessary to inject additional fuel behind the fuselage to increase the thrust and increase the speed and lift of the aircraft. The combustion chamber of this additional injected fuel is called afterburner room. Afterburner can quickly increase the basic thrust of the engine in the shortest time, and improve the performance of the aircraft such as take-off, climb and rapid acceleration during combat without increasing the windward area o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/52C04B35/622C04B41/89F23R3/18
CPCC04B35/52C04B35/571C04B35/622C04B35/80C04B41/52C04B41/89C04B2235/3826C04B2235/6567C04B2235/658C04B2235/6582C04B2235/77F23R3/18C04B41/5096C04B41/4529C04B41/5024C04B41/4527
Inventor 罗瑞盈王佳妮
Owner BEIHANG UNIV
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