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Method for predicting tensile strength of woven ceramic-based composite material

A composite material and prediction method technology, which is applied in the direction of applying stable tension/pressure to test the strength of materials, can solve the problems of large difference in actual strength and unsatisfactory prediction results, and achieve accurate prediction results

Active Publication Date: 2019-05-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Description
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AI Technical Summary

Problems solved by technology

Among the above prediction tools, strength prediction is widely used, but the existing prediction methods are far from the actual strength of woven ceramic matrix composites, and the prediction results are not ideal.

Method used

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  • Method for predicting tensile strength of woven ceramic-based composite material
  • Method for predicting tensile strength of woven ceramic-based composite material
  • Method for predicting tensile strength of woven ceramic-based composite material

Examples

Experimental program
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Effect test

Embodiment 1

[0177] Taking the 2D C / SiC braided ceramic matrix composite material as the test sample, test the tensile strength of the sample in a high temperature environment of 700°C under different oxidation times, and draw the test curve of the relationship between the tensile strength of the test sample and the oxidation time;

[0178] Predict the tensile strength of the test sample using the following parameters: V f = 40%, E f =200GPa, E m =350GPa, r f = 3.5 μm, ζ d =1.2J / m 2 , τ 0_i =6MPa,τ 0_f =1MPa, α rf =7×10 -6 / °C, α lf =1×10 -6 / °C,α rm = α lm =4.8×10 -6 / °C, ΔT=-1000°C, m f =5.

[0179] Substituting the above parameters into the established matrix crack plane load bearing relationship equation, the simulation curve of the relationship between the tensile strength and oxidation time of the ceramic matrix composite material is obtained, as shown in figure 2 shown. Depend on figure 2 It can be seen that the degree of coincidence between the simulation curve a...

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Abstract

The invention belongs to the technical field of composite material tensile strength prediction, and particularly relates to a method for predicting the tensile strength of a woven ceramic matrix composite material. On the basis of considering the temperature and oxidation influence, a fiber / matrix interface debonding length equation and a fiber slippage length equation are established by adoptinga fracture mechanics method, and a stress distribution equation after matrix cracking and interface debonding damage of the woven ceramic matrix composite is considered; on the basis of total load bearing criterion, by combining the equations, a fiber / matrix interface oxidation area fiber fracture probability equation, a fiber / matrix interface debonding area fiber fracture probability equation anda fiber / matrix interface bonding area fiber fracture probability equation are established respectively, to obtain a fiber fracture probability and stress relation equation. The method is used for predicting the tensile strength of the woven ceramic matrix composite material, and the prediction result is higher in accuracy.

Description

technical field [0001] The invention belongs to the technical field of composite material tensile strength prediction, in particular to a method for predicting the tensile strength of a braided ceramic matrix composite material. Background technique [0002] Braided ceramic matrix composites have the advantages of high temperature resistance, corrosion resistance, low density, high specific strength, and high specific modulus. Compared with superalloys, they can withstand higher temperatures, reduce cooling airflow, and improve turbine efficiency. They have been used in aviation Engine combustion chamber, turbine guide vane, turbine shell ring, tail nozzle, etc. The LEAP (Leading Edge Aviation Propulsion, LEAP) series engine developed by CFM company, the high-pressure turbine uses braided ceramic matrix composite material components, the LEAP-1B engine provides power for Airbus A320 and Boeing 737MAX, and the LEAP-X1C engine is also used by my country's large aircraft C919 t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/18
Inventor 李龙彪
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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