| 摘要 |
Aspects of the disclosure are directed to a liner (400, 500) associated with a combustor of an aircraft engine, comprising: a thermal barrier coating (426, 436; 526, 536), and a base metal (446, 546), wherein the thermal barrier coating (426, 436; 526, 536) comprises a contoured surface on a flowpath side proximate to an exit of a hole (306) formed by the thermal barrier coating (426, 436; 526, 536) and the base metal (446, 546). |
