Abstract: The combustor linear is a typical hot-section component of a gas turbine engine. Design, fabrication, and testing validation of SiC/SiC combustor linear were conducted. The 2.5D-SiC fiber preforms were used as the reinforcement for the SiC/SiC combustor linear, and the BN interphase was deposited on the surface of the 2.5D-SiC fiber preforms using the chemical vapor infiltration (CVI) process to enhance the damage tolerance of the combustor linear structure. The SiC matrix was deposited using the CVI + precursor infiltration and pyrolysis (PIP) hybrid process to reduce the internal porosity and improve the density of SiC matrix. The air film holes were machined using the ultrasonic vibration assisted machining and the combustor linear was assembled through high temperature ceramic glue assisted riveting. Ground bench tests were conducted, and the outlet temperature distributions were monitored for seven different operating conditions (e.g., inlet pressure and temperature). The average outlet temperature of the tested combustor linear reached 1500°C, with the highest temperature approaching 1700°C. The integrity of the SiC/SiC combustor liner remained after testing. The inner and outer SiC/SiC combustor liners were detected for damage using micro-CT section scanning after the bench test, with the large-sized pores in inner combustor liner mainly concentrated near the largest air film hole; the defect forms of outer combustor liner mainly consisted of delamination, concentrating at the thicker bottom region.