Preparation method of SiCf/SiC ceramic matrix composite turbine blades

A technology of turbine blades and composite materials, which is applied in the field of composite material parts manufacturing, can solve problems such as high density, limited operating temperature, and restricted engine performance, and achieve the effect of improving the silicon corrosion resistance of fibers

Inactive Publication Date: 2013-05-22
XI AN JIAOTONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, the nickel-based superalloy used in aero-engine turbine blades has a limite...

Method used

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  • Preparation method of SiCf/SiC ceramic matrix composite turbine blades
  • Preparation method of SiCf/SiC ceramic matrix composite turbine blades
  • Preparation method of SiCf/SiC ceramic matrix composite turbine blades

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0053] see figure 1 , the preparation method of fiber toughened SiC ceramic matrix composite material turbine blade, comprises the following steps:

[0054] 1. Analyze the working stress of parts

[0055] Firstly, the stress distribution of the parts under the service conditions is analyzed, and the parts are divided into different regions according to the stress range, and the material structure of different regions is different. Design a material unit structure that meets the characteristics of light-curing rapid prototyping technology, and obtain its performance requirements for local materials by analyzing the state of the parts under service conditions. Each region is integrated to finally obtain a stress balance model, which can be regarded as a weaving model of the reinforcement (SiC fiber), and then the three-dimensional data of the fiber-guided scaffold with a spatial topology is obtained through CAD modeling.

[0056] 2. Fabrication of internal supports and negati...

Embodiment 2

[0082] see figure 1 , the preparation method of fiber toughened SiC ceramic matrix composite material turbine blade, comprises the following steps:

[0083] Steps 1 and 2 are the same as in Example 1.

[0084] 3. Preparation of ceramic slurry

[0085] 3.1 Preform solution preparation

[0086] The monomer and crosslinking agent used in gel injection molding are acrylamide and N,N'-methylenebisacrylamide respectively. The initiator adopts ammonium persulfate as the initiator and tetramethylethylenediamine as the catalyst. Sodium polyacrylate was used as a dispersant.

[0087] First, the monomer acrylamide (AM, analytically pure) and the cross-linking agent N,N'-methylenebisacrylamide (MBAM, analytically pure) are made into a pre-preparation solution for gel injection molding, and the monomer and The mass ratio of the cross-linking agent is 6-10:1, and the content of the monomer and the cross-linking agent is 12-20% of the total mass of the solution.

[0088] 3.2 Preparati...

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Abstract

The invention discloses a preparation method of SiCf/SiC ceramic matrix composite turbine blades, which is characterized in that through analyzing the stress distribution of a blade in an application state, based on this point, a performance-controllable SiCf/SiC ceramic matrix composite turbine blade is manufactured through the designing and adopting of processes such as rapid forming, high-performance continuous yarn braiding, gel-casting, reactive sintering, and the like. According to the method, parts such as blades and the like are manufactured by using heterogeneous materials, the contradiction between the uniformity and nonuniform loaded structure of materials is solved, and the performances of materials can be set flexibly according to the bearing needs of manufactured parts; and prepared SiCf/SiC ceramic matrix composite turbine blades have the characteristics of near-net forming variable-cross-section complex structure, controllable material performance, flexible machining, short production cycle, low cost, and the like, and can be applied to the development and manufacturing of high-temperature-resistant complex structured parts for aerospace and the like.

Description

technical field [0001] The invention belongs to the technical field of composite material parts manufacturing, and relates to a SiC f / SiC ceramic matrix composite material turbine blade preparation method. Background technique [0002] At present, the nickel-based superalloy used in aero-engine turbine blades has limited service temperature and high density, which restricts the further improvement of engine performance. The continuous fiber braided toughened SiC ceramic matrix composite blade has the characteristics of high temperature resistance, high toughness, high specific strength and low density, which can greatly improve the thrust-to-weight ratio and high-temperature performance of the engine. It is an ideal material for the manufacture of high-temperature parts of the engine in the future. Contents of the invention [0003] The problem solved by the present invention is to provide a SiC f A method for preparing a turbine blade of a SiC ceramic matrix composite ...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/565C04B35/622
Inventor 鲁中良李涤尘陆峰曹继伟卢秉恒
Owner XI AN JIAOTONG UNIV
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