Abstract: Turbine rotor is the key component of gas turbine engines. Design, fabrication, and experimental verification of SiC/SiC turbine blisk were investigated. The Spider Web Structure (SWS) SiC preform was used as the reinforcement in turbine blisk. The BN interphase and SiC matrix were deposited on the surface of the SWS SiC fiber preform, respectively. The SiC/SiC turbine blisk was machined by "on-line processing" to form a turbine bisk that meets the design requirements. The environmental barrier coatings (EBCs) were prepared on the surface of SiC/SiC turbine blisk using the atmospheric plasma spraying (APS) method. The CT scan was conducted to characterize the internal defects in SiC/SiC turbine blisk. The mechanical performance evaluation, over rotation test and engine bench test were performed, respectively. The maximum failure strength approached 300 MPa. During the over rotation test, when the rotating speed reached n=104166 r/min, the blade in the turbine blisk broke; and when the rotating speed reached n=108072 r/min, the disk in the turbine blisk broke. During the engine bench test, low cyclic fatigue of N=994 cyclic with maximum speed n_max=60000 r/min and N=100 cyclic with maximum speed n_max=70000 r/min were completed. On January 1, 2022, the SiC/SiC turbine blisk successfully completed the first flight test in Zhuzhou, which is also the first flight test of the domestic SiC/SiC rotor assembly platform and verified the feasibility of SiC/SiC turbine rotor application in gas turbine engines.