| 摘要 |
The present invention relates to a combustor liner (300) for a gas turbine, the combustor liner having a cylindrical shape and comprising two sections, wherein the upstream section (310) with respect to the hot gas flow during operation is ring shaped and comprises a rounded lip section (330) and a trailing section (340), and wherein an inner radius (R1) of the trailing section (340) is increasing along a centerline of the liner in the direction of the hot gas flow during operation. The invention also relates to a combustor (400) and a gas turbine comprising such combustor. |
