| 摘要 |
A system, in one embodiment, includes a turbine combustor liner (34). The combustor liner (34) includes a patterned surface (62) at a downstream end portion (52) relative to a downstream direction of combustion along a longitudinal axis of the turbine combustor liner (34). The patterned surface (62) includes a plurality of discrete protrusions (72) in both axial and circumferential directions about the downstream end portion (52) relative to the longitudinal axis of the turbine combustion liner (34).
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