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Aeroengine ceramic matrix composite fixed guide vane structure and its molding

An aero-engine and composite material technology, which is applied in engine components, machines/engines, air transportation, etc., can solve problems such as poor blade root strength and unreasonable design of CMC guide vane prefabricated bodies, so as to reduce costs and reduce manufacturing risks. , good craftsmanship effect

Active Publication Date: 2022-07-12
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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  • Aeroengine ceramic matrix composite fixed guide vane structure and its molding
  • Aeroengine ceramic matrix composite fixed guide vane structure and its molding
  • Aeroengine ceramic matrix composite fixed guide vane structure and its molding

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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) Preform preparation: 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 to a suitable size according to the size of the part, and the multi-layered 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 interfa...

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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 fixed guide vane structure and its molding, and belongs to the technical field of aero-engine fixed guide preparation. The turbine guide vane is prepared by an integrated assembly method, the parts are integrated by riveting, and the assembly structure adopts a SiC ceramic matrix to realize "welding", so as to avoid the defect of insufficient strength of the blade root caused by the conventional sewing-molded prefab; After the protrusions on the edge plate and the second lower edge plate are directly riveted with the blades, they are then riveted with the third lower edge plate and the fourth lower edge plate by riveting rivets, and the SiC ceramic matrix is ​​deposited on the entire product by the CVI process. Complete the integration preparation. The SiC / SiC high-pressure guide vane has good manufacturability, the preparation of the edge plate and the vane is simpler, and the installation is more reliable. This structure can be fully applied to small engines, such as civil turboshaft engines and turbojet engines.

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 temperature of the gas before the turbine of the engine with a thrust-to-weight ratio of 10 in developed countries reaches 1850-1950K, which can generate more than double the thrust than the previous generation of aero-engines; in the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D9/04F01D25/00C04B35/565C04B35/622C04B35/80
CPCF01D9/041F01D25/005F01D25/00C04B35/565C04B35/622Y02T50/60
Inventor 涂建勇王佳民许建锋刘梦珠郭洪强成来飞
Owner XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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