Method for preparing integral turbine blade disc based on SiC fiber ceramic matrix composite material

A technology of turbine blisks and composite materials, which is applied in mechanical equipment, blade support elements, engine elements, etc., can solve problems such as poor practicability, and achieve the effects of good practicability, high-density preparation, and shortened preparation cycle.

Inactive Publication Date: 2019-04-19
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to overcome the shortcomings of poor practicability of the existing integral turbine blisk preparation method, th

Method used

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  • Method for preparing integral turbine blade disc based on SiC fiber ceramic matrix composite material

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0020] (1) Using SiC fibers as raw materials, place the warp SiC fibers at equiangular intervals with the origin of the polar coordinates as the center of the circle, and finally form a circular warp fiber arrangement, and the end of each warp fiber is fixed in the ring by elastic leads. On the tooling, the warp fiber arrangement density is designed according to the target load.

[0021] Starting from the center of the circle, the latitudinal SiC fibers are interwoven up and down with two bundles of adjacent meridional fibers, and are wound continuously outward one by one in the circumferential direction. The weft fiber winding density is designed according to the target load.

[0022] As the number of weft fiber rings increases, the angle between two warp fibers gradually increases, and yarn is evenly added at the angle between two adjacent warp fibers to ensure the local volume fraction of warp and weft fibers in the fabric. Consistently until the desired diameter circular f...

Embodiment 2

[0031] (1) Using SiC fibers as raw materials, place the warp SiC fibers at equiangular intervals with the origin of the polar coordinates as the center of the circle, and finally form a circular warp fiber arrangement, and the end of each warp fiber is fixed in the ring by elastic leads. On the tooling, the warp fiber arrangement density is designed according to the target load.

[0032] Starting from the center of the circle, the latitudinal SiC fibers are interwoven up and down with two bundles of adjacent meridional fibers, and are wound continuously outward one by one in the circumferential direction. The weft fiber winding density is designed according to the target load.

[0033] As the number of weft fiber rings increases, the angle between two warp fibers gradually increases, and yarn is evenly added at the angle between two adjacent warp fibers to ensure the local volume fraction of warp and weft fibers in the fabric. Consistently until the desired diameter circular f...

Embodiment 3

[0042] (1) Using SiC fibers as raw materials, place the warp SiC fibers at equiangular intervals with the origin of the polar coordinates as the center of the circle, and finally form a circular warp fiber arrangement, and the end of each warp fiber is fixed in the ring by elastic leads. On the tooling, the warp fiber arrangement density is designed according to the target load.

[0043] Starting from the center of the circle, the latitudinal SiC fibers are interwoven up and down with two bundles of adjacent meridional fibers, and are wound continuously outward one by one in the circumferential direction. The weft fiber winding density is designed according to the target load.

[0044] As the number of weft fiber rings increases, the angle between two warp fibers gradually increases, and yarn is evenly added at the angle between two adjacent warp fibers to ensure the local volume fraction of warp and weft fibers in the fabric. Consistently until the desired diameter circular f...

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Abstract

The invention discloses a method for preparing an integral turbine blade disc based on a SiC fiber ceramic matrix composite material, which is used for solving the technical problem of the poor practicability of the existing integral turbine blade disc preparation method. The technical scheme is as follows. Firstly, a plane polar coordinate weaving method is adopted to prepare a turbine blade discprefabricated body unit layer, so that continuous SiC fibers are arranged in two principal stress directions in the warp direction and the weft direction. Then Z-direction puncture, sewing and die pressing are adopted to finish the shaping of the prefabricated body. A BN interface layer is prepared on the surface of the SiC fiber of the prefabricated body by utilizing a chemical vapor infiltration method. The prefabricated body of the turbine disc is pre-densified by adopting a chemical vapor infiltration process. The turbine disc blade is processed by adopting a cubic boron nitride or diamond special cutter on a multi-axis numerical control machine tool. Finally, an anti-oxidation coating is prepared. As the prefabricated body is provided with the continuous SiC fibers in two main principal directions in the warp direction and the weft direction, the bearing performance of the integral turbine blade disc is improved, the preparation period of the integral turbine blade disc is shortened, and the practicability is good.

Description

technical field [0001] The invention relates to a method for preparing an integral turbine blisk, in particular to a method for preparing an integral turbine blisk based on a SiC fiber ceramic matrix composite material. Background technique [0002] Document 1 "Nakamura T, Oka T, Imanari K, et al.Development of CMC turbineparts for aero engines[J].IHI Engineering Review, 2014,47(1):29-32."The study believes that ceramic matrix composites have Low density, high specific strength, high specific stiffness, high hardness, high wear resistance, high service temperature, large thermal conductivity, small thermal expansion coefficient, strong oxidation resistance, good vibration absorption performance, etc. The application potential is huge. [0003] With the development of high-performance aircraft technology, higher requirements are put forward for the fuel efficiency, turbine temperature, and service life of aero-engines; conventional high-temperature alloy turbine blisks are g...

Claims

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Application Information

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IPC IPC(8): C04B35/80C04B35/565C04B35/571F01D5/02F01D5/28
CPCC04B35/806C04B35/565C04B35/571C04B2235/3826C04B2235/386C04B2235/5244C04B2235/656C04B2235/6567C04B2235/658C04B2235/96F01D5/02F01D5/282F01D5/284
Inventor 刘持栋刘小冲刘永胜董宁孙肖坤刘小瀛陈博成来飞
Owner NORTHWESTERN POLYTECHNICAL UNIV
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