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Engine turbine outer ring made of multi-element and multi-layer self-healing ceramic matrix composite

A composite material and ceramic-based technology, applied to engine components, machines/engines, layered products, etc., can solve problems such as failure of fiber/SiC parts, large difference in thermal expansion coefficient, etc., to reduce maximum stress, improve demand, and control cracks the formation of the effect

Active Publication Date: 2018-07-24
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] For traditional multi-layer self-healing ceramic matrix composites, due to the large difference in thermal expansion coefficients of fibers, SiC, BC4, etc., cracks are easily generated between them due to thermal expansion mismatch to form rapid diffusion channels for oxygen, resulting in failure of fiber / SiC parts

Method used

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  • Engine turbine outer ring made of multi-element and multi-layer self-healing ceramic matrix composite
  • Engine turbine outer ring made of multi-element and multi-layer self-healing ceramic matrix composite
  • Engine turbine outer ring made of multi-element and multi-layer self-healing ceramic matrix composite

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Experimental program
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Effect test

Embodiment 1

[0035] This embodiment provides a multi-layer multi-layer self-healing ceramic matrix composite engine turbine outer ring, the turbine outer ring is made of fiber reinforced ceramic matrix composite material; fiber reinforced ceramic matrix composite material is sequentially composed of silicon carbide fiber layer, the first A base layer and a second base layer; wherein, the first base layer is an aluminum nitride layer; the second base layer consists of alternately deposited silicon carbide layers and self-healing layers BC 4 Layer composition, the number of alternate depositions is 2 times. That is to say, the fiber-reinforced ceramic matrix composite material in this embodiment includes: silicon carbide fiber layer, aluminum nitride layer, silicon carbide layer, BC 4 layer, SiC layer and BC 4 layer, the thickness of the silicon carbide fiber layer is 4 μm, the thickness of the aluminum nitride layer is 2 μm, and the thickness of each silicon carbide layer and the respectiv...

Embodiment 2

[0044] Carry out ANSYS finite element simulation with the traditional multi-layer self-healing ceramic matrix composite material and the improved composite material (the multi-layer self-healing ceramic matrix composite material provided by Embodiment 1 of the present invention), and analyze the two components after cooling at high temperature. The distribution of residual stress during the process. The specific analysis process is as follows.

[0045] 1. Microscopic model establishment of multi-layer self-healing ceramic matrix composites

[0046] For the traditional multi-layer self-healing ceramic matrix composite, its structure is: silicon carbide fiber / silicon carbide / self-healing layer / silicon carbide / self-healing layer / silicon carbide, wherein the self-healing layer is BC4 layer, For the improved multi-layer self-healing ceramic matrix composite, the result is silicon carbide fiber / aluminum nitride / silicon carbide / self-healing layer / silicon carbide / self-healing layer, ...

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Abstract

The invention relates to an engine turbine outer ring made of a multi-element and multi-layer self-healing ceramic matrix composite. The turbine outer ring is made of the fiber-reinforced ceramic matrix composite. The fiber-reinforced ceramic matrix composite is sequentially composed of a fiber layer, a first matrix layer and a second matrix layer, wherein the first matrix layer is an aluminum nitride layer and is provided with fibers carbon fibers and / or silicon carbide fibers. According to the engine turbine outer ring made of the multi-element and multi-layer self-healing ceramic matrix composite, an AlN ceramic interface layer is additionally arranged between the fibers of the multi-element and multi-layer self-healing ceramic matrix composite and a silicon carbide matrix, so that themaximum stress in the turbine outer ring is reduced, energy in the composite is effectively released in the cooling process, formation of cracks is controlled, and the requirements of engines and especially high-performance aircraft engines can be better met.

Description

technical field [0001] The invention relates to the technical field of ceramic matrix composite materials, in particular to a multi-component multi-layer self-healing ceramic matrix composite material engine turbine outer ring. Background technique [0002] With the development of civil and military aero-engines, the requirements for aero-engines are getting higher and higher, such as the thrust-to-weight ratio is getting higher and higher. The main way for the turbojet engine to increase the thrust-to-weight ratio is to reduce the weight and increase the temperature before the turbine, so that the high-temperature strength, corrosion resistance and oxidation resistance of the internal components of the engine are required to be higher and higher. The outer ring of the engine turbine is the main stator of the turbine. Parts, withstand high temperature and high pressure, require free expansion and wear resistance, so as to adapt to the expansion of the casing and the proper g...

Claims

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Application Information

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IPC IPC(8): F01D9/00B32B9/00B32B9/04B32B15/04B32B33/00
CPCB32B5/02B32B5/08B32B9/041B32B9/047B32B9/048B32B15/04B32B33/00B32B2262/10B32B2262/106B32B2262/14B32B2264/102B32B2264/108B32B2264/12B32B2307/762B32B2605/18F01D9/00
Inventor 罗瑞盈邓楚燕
Owner BEIHANG UNIV
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