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A high-temperature static fatigue damage prediction method for braided ceramic matrix composites

A technology for composite materials, predictive methods, applied in the direction of analyzing materials, testing material strength using applied stable tension/compression, measuring devices, etc.

Active Publication Date: 2021-05-14
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] At present, there are few studies on the high-temperature static fatigue damage of braided ceramic matrix composites. How to consider the influence of high-temperature static fatigue on the internal damage of braided ceramic matrix composites and monitor the damage caused by high-temperature loads to composite materials is the key to the structure of braided ceramic matrix composites. Key technical issues to be solved in practical engineering applications

Method used

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  • A high-temperature static fatigue damage prediction method for braided ceramic matrix composites
  • A high-temperature static fatigue damage prediction method for braided ceramic matrix composites
  • A high-temperature static fatigue damage prediction method for braided ceramic matrix composites

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Embodiment 1

[0082] The static fatigue damage evolution process of braided C / [Si-B-C] ceramic matrix composites under high temperature 1200℃ air environment was predicted.

[0083] Material basic parameters: V f = 40%, r f =3.5μm,E f =220GPa,E m =200GPa,α f =-0.38×10 -6 / °C,α m =-4.6×10 -6 / °C,τ i =15MPa,τ f =3MPa.

[0084] The result is as figure 2 as shown, figure 2 (a) is the high temperature static fatigue hysteresis loop of the composite material, and (b) is the high temperature static fatigue damage evolution curve of the composite material. according to figure 2 It can be seen that the predicted curve obtained by the present invention is very close to the experimental data, indicating that the prediction method provided by the present invention can accurately predict the high temperature static fatigue damage condition of the braided ceramic matrix composite.

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Abstract

The invention relates to the technical field of damage evolution prediction of braided ceramic matrix composite materials, and provides a method for predicting the evolution of high temperature static fatigue damage of braided ceramic matrix composite materials. The invention firstly establishes the axial stress distribution equation of the inner fiber of the composite material under the action of high temperature static fatigue load Then, based on the interface debonding criterion of fracture mechanics, the debonding length equation and slip length equation of the composite material high temperature static fatigue interface were established, and finally the hysteretic constitutive relation equation of braided ceramic matrix composites under high temperature static fatigue load was established, and the hysteretic dissipation energy was used to predict High temperature static fatigue damage evolution of braided ceramic matrix composites. The prediction method provided by the invention comprehensively considers the effects of high-temperature static fatigue on interface debonding, interface oxidation, and interface slippage of the braided ceramic matrix composite material, and can accurately predict the high-temperature static fatigue damage evolution curve of the braided ceramic matrix composite material.

Description

technical field [0001] The invention relates to the technical field of damage evolution prediction of braided ceramic matrix composite materials, in particular to a method for predicting high temperature static fatigue damage evolution of braided ceramic matrix composite materials. 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 uses braided ceramic matrix composite material components for the high-pressure turbine. The LEAP-1B engine provides power for Airbus A320 and Boeing 737MAX. The only power u...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N3/18
CPCG01N3/18G01N2203/0073G01N2203/0096G01N2203/0218G01N2203/0226G01N2203/0676
Inventor 李龙彪
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS