Aero-engine ceramic matrix composite fixation guider blade structure and molding method thereof

Abstract

The invention belongs to the technical field of preparation of an aero-engine fixation guider, relates to an aero-engine ceramic matrix composite fixation guider blade structure and a molding method thereof, and is to overcome the structural defects that an existing CMC guider blade prefabricated body is unreasonable in design and poor in blade root strength. A turbine guider blade manufactured in an integrated assembly mode comprises multiple stages of guide blades, parts are integrally assembled in a riveting mode, and an assembly structure adopts a SiC ceramic matrix to achieve welding; aneffective space between an upper edge plate and an outer casing is fully utilized, the blade body and the upper edge plate are installed and positioned through limiting rivets and a limiting table, the SiC ceramic matrix is deposited on the whole product through the CVI technology, and integrated preparation is completed; by means of the structure, the complex SiC / SiC multi-connected high-pressure guide blade has good manufacturability, the edge plate and the blade are easier to manufacture and more reliable to install, and the dimensional precision of a final product is easier to guarantee;and the structure can be fully applied to medium-sized and large-sized engines and five-generation engines.

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...

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

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