SiC

f

/SiC composites combustor liner which consists of inner liner

outer liner

left and right plate prepared by chemical vapour infiltration process (CVI)

was exposed to simulated aero-engine service environment by sector combustor rig. A three-layer BSAS/Mullite/Si environmental barrier coating (EBC) was deposited on the flow surface of the combustor liner by atmospheric plasma spraying. The evolution of the defect

mechanical property

microstructure and surface pha

se composition of the composite liner subjected to combustion environment were evaluated by mechanical test

scanning electron microscope and X-ray diffraction

respectively. The results indicate that the as-sprayed coating is mainly composed of monoclinic celsian BSAS phase and BaAl

2

O

4

phase; After the sector combustor test

the core ablation area is mainly composed of orthorhombic mullite phase Al

2

（Al

2.8

Si

1.2

）O

9.6

cubic Si

and BaAl

2

O

4

phases. Meanwhile

silicon droplets and holes can also be observed on the surface. In addition

the results of mechanical properties after the burner rig test show that the tensile strength of SiC

f

/SiC composites in the coating integrity area is not affected

while that of the core ablation area decreased significantly. The high-temperature ablation mechanism of the coating was discussed at final.