Nanjing University of Aeronautics and Astronautics

Guoqiang Yu

Yingdong Song

Xiguang Gao

Sheng Zhang

Yunfa Jia

Chuyang Xie

Fangxiao Song

Jinkang Du

Chenyang Liu

Hongnian Dong

Chengqian Dong

Chao You

Zheng Ni

Xiaoting Shi

Lu Zhang

The present disclosure provides an optimized designing method for a laminate preform of a ceramic matrix composite e. With overall consideration of a strength requirement of a component, a geometric shape and properties of the laminate preform, the method includes: optimizing, based on a corresponding mechanical formula, a fiber volume fraction of each laminate constituting the preform and a fiber direction in the laminate, and selecting a preferred microscopic structure for each laminate, thereby taking full advantage of material performance. The method is applicable for optimized design of various components of the ceramic matrix composite.

Optimized designing method for laminate preform of ceramic matrix composite

A method is provided for calculating gaseous diffusion and oxidation evolution of a ceramic matrix composite (CMC) structure, which includes determining temperature and load distribution in a structural member; determining matrix crack distribution in the structure; establishing an equivalent diffusion coefficient model of a fiber bundle scale to predict a gas flow channel in a fiber bundle: averaging a total amount of gaseous diffusion in the channel to establish the equivalent diffusion coefficient model of the fiber bundle composite scale related to the matrix crack distribution; establishing a representative volume element (RVE) model; establishing an equivalent diffusion coefficient model of a RVE scale; calculating the distribution of the gas concentration and oxidation products in the structure; calculating a growth thickness of an oxide at cracks and pores in each element; and updating sealing conditions of the gas channel, and calculating a new equivalent diffusion coefficient field and the distribution of the oxidation products again.

Method for calculating gaseous diffusion and oxidation evolution of ceramic matrix composite (CMC) structure

A high-temperature biaxial strength tester for a CMC turbine vane includes a test stand, a thermal insulation box, a vane fixture, a biaxial loading device, thermocouples, a multi-channel thermometer, quartz lamps, a digital image correlation (DIC) system, and a cooling circulation system. The biaxial loading device includes two loading mechanisms arranged at 90&#xb0; to each other. Each of the two loading mechanisms includes an electric cylinder and a ceramic push rod. One end of the ceramic push rod is connected to the electric cylinder, and the other end of the ceramic push rod extends into the thermal insulation box to contact an outer platform of the CMC turbine vane. The electric cylinder is provided with a load-displacement sensor. The thermocouples are arranged on the thermal insulation box. The quartz lamps are arranged inside the thermal insulation box. The multi-channel thermometer is connected to the thermocouples.

High-temperature biaxial strength tester for ceramic matrix composite (CMC) turbine vane and test method thereof

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Nanjing, China

Guoqiang Yu