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Ceramic matrix composite material fixing guider blade structure of aircraft engine and molding thereof

A technology of aero-engine and composite materials, which is applied to engine components, machines/engines, stators, etc., can solve the problems of unreasonable design of CMC guide vane prefabricated body, poor blade root strength, etc. Process adaptable effect

Active Publication Date: 2020-04-10
XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to overcome the structural defects of unreasonable design of the existing CMC guide vane prefabricated body and poor blade root strength, the present invention provides a novel ceramic matrix composite material fixed guide vane structure and its forming method

Method used

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  • Ceramic matrix composite material fixing guider blade structure of aircraft engine and molding thereof
  • Ceramic matrix composite material fixing guider blade structure of aircraft engine and molding thereof
  • Ceramic matrix composite material fixing guider blade structure of aircraft engine and molding thereof

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Embodiment 1

[0055] The size of the CMC fixed guide vane in this embodiment: length 60mm, width 50mm, height 120mm. The raw material of the ceramic matrix composite material in this embodiment is SiC fiber, and the raw material used in the preparation process is trichloromethylsilane and H 2 , Ar gas, etc.

[0056] Specific steps are as follows:

[0057] (1) Preparation of prefabricated body: SiC fiber is used to weave 2D plain weave cloth, and other prefabricated body types such as 2.5D and 3D can also be used. Cut the plain weave into an appropriate size according to the size of the part, stack multiple layers of plain weave, and puncture in the stacking direction of the plain weave. The punctured fiber uses the same SiC fiber to form a SiC fiber prefabricated body. The SiC fiber preform is fixed and molded by using a mold.

[0058] (2) Interface layer preparation: the prefabricated body in step (1) is placed in a chemical vapor deposition furnace to prepare an interface layer. The b...

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Abstract

The invention relates to a fixing guider blade structure and molding thereof, in particular to a ceramic matrix composite material fixing guider blade structure of an aircraft engine and molding thereof, and belongs to the technical field of preparation of fixing guiders of aircraft engines. According to the fixing guider blade structure and the molding thereof, the structural defects of unreasonable design and poor root strength of an existing CMC guider blade prefabricated body are overcome, a turbine guider blade is prepared by adopting an integrated assembly mode, parts are integrally assembled by adopting a riveting mode, the assembly structure adopts a SiC ceramic matrix to realize welding, and then the defect of insufficient root strength caused by conventional sewing the molded prefabricated body is avoided; and multi-part backup and assembly optimization can be realized, the risk of whole component scrapping caused by single part scrapping can be avoided, the preparation riskis reduced, the cost is reduced, and the component quality is improved.

Description

technical field [0001] The invention relates to a structure and molding of a fixed guide blade, in particular to an assembly structure and a forming method of a fixed guide blade of a ceramic matrix composite material for an aero-engine, and belongs to the technical field of preparation of an aero-engine fixed guide. Background technique [0002] The demand for high-performance aeroengines for military and civilian aircraft is increasingly urgent. There are two main ways to improve the performance of the engine. One is to increase the boost ratio of the compressor, and the other is to increase the gas temperature at the turbine inlet. As the gas temperature at the turbine inlet increases, the high temperature components of the engine need to bear greater heat load. The gas temperature in front of the turbine of an engine with a thrust-to-weight ratio of 10 in developed countries can reach 1850-1950K, which can generate more than double the thrust of the previous generation o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04F01D25/00C04B35/565C04B35/80C04B35/622
CPCF01D9/041F01D25/005C04B35/565C04B35/62868C04B35/622C04B2235/5244C04B2235/5256C04B2235/608F05D2230/314F05D2300/6033
Inventor 涂建勇王佳民何江怡陈旭田录录曹懿辰成来飞
Owner XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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