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Structure and Forming of Aeroengine Ceramic Matrix Composite Fixed Guide Vane

An aero-engine and composite material technology, which is applied in the direction of engine components, machines/engines, stators, etc., can solve problems such as poor blade root strength, unreasonable design of CMC guide blade prefabrication, etc., to reduce costs, reduce manufacturing risks, The effect of improving component quality

Active Publication Date: 2022-06-21
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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  • Structure and Forming of Aeroengine Ceramic Matrix Composite Fixed Guide Vane
  • Structure and Forming of Aeroengine Ceramic Matrix Composite Fixed Guide Vane
  • Structure and Forming of Aeroengine Ceramic Matrix Composite Fixed Guide Vane

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Embodiment 1

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

[0056] Specific steps are as follows:

[0057] (1) Preparation of preforms: SiC fibers are woven into 2D plain weave fabrics, and other preform types such as 2.5D and 3D can also be used. The plain weave fabric is cut into a suitable size according to the size of the part, and the multi-layer plain weave fabrics are stacked, and punctured in the stacking direction of the plain weave fabrics. The same SiC fibers are used for the punctured fibers to form a SiC fiber preform. The SiC fiber preform is fixed and shaped using a mold.

[0058] (2) Preparation of the interface layer: the preform in step (1) is placed in a chemical vapor deposition furnace to prepare the in...

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Abstract

The invention relates to a fixed guide vane structure and molding, in particular to an aero-engine ceramic matrix composite material fixed guide vane structure and its forming, and belongs to the technical field of aero-engine fixed guide preparation. To overcome the structural defects of unreasonable design of the existing CMC guide vane prefabrication and poor blade root strength, the turbine guide vane is prepared by integrated assembly method, the parts are integrated and assembled by riveting, and the assembly structure uses SiC ceramic matrix to realize "welding", avoiding The defect of insufficient blade root strength caused by conventional sewing-molded prefabricated body. It can realize the characteristics of multi-part backup and optimal assembly, which can avoid the risk of scrapping the entire component caused by the scrapping of a single part, reduce the risk of preparation, reduce the cost, and improve the quality of the component.

Description

technical field [0001] The invention relates to a structure and molding of a fixed guide vane, in particular to an assembling structure and a molding method of a ceramic matrix composite fixed guide vane for aero-engine, and belongs to the technical field of aero-engine fixed guide preparation. Background technique [0002] The demand for high-performance aero-engines for military and civil 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 temperature of the turbine inlet gas. As the turbine inlet gas temperature increases, the high temperature components of the engine are subject to greater thermal loads. The current engine with a thrust-to-weight ratio of 10 has a gas temperature of 1850-1950K before the turbine, which can generate more than double the thrust of the previous generation of aero-engines; the thrust-to-weight ratio of the fif...

Claims

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Application Information

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Patent Type & Authority Patents(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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