Abstract: Turbine shroud is a typical hot-section static component of aero-engine, and it is also the first hot-section component of ceramic-matrix composites (CMCs) to realize engineering applications. The design of SiC/SiC turbine shroud fiber preforms, boron nitride (BN) interphase and SiC matrix deposition methods, precision processing of air film holes, and gas environment thermal shock experimental methods were investigated. The SiC fiber preforms of turbine shrouds were prepared by two-dimensional fiber preforms and needle-punching process, and the chemical vapor infiltration (CVI) was used to deposit the BN interphase on the surface of the SiC fiber preforms. The SiC matrix was also deposited by the CVI process, and the air film holes, and surface square grooves of SiC/SiC turbine shroud were processed by the laser micromachining technology. After the processing and molding, the gas environment thermal shock experiments were conducted at 1350, 1400, and 1450℃, respectively. During the experiments, the surface temperatures of the turbine shrouds were monitored using the infrared thermal imaging, and the temperature-time curves were obtained. The temperature change rates in the heating, holding and cooling stages and the damage patterns caused by temperature changes were analyzed. After the experiments, the surfaces of SiC/SiC turbine shrouds were observed using scanning electron microscopy (SEM) for microscopic damage, and the internal damage was analyzed using X-ray computed tomography (XCT) to reveal its damage mechanisms under different temperature thermal shock environments.