| 摘要 |
The present invention relates to a combustor transition portion (24) configured to guide combustion gases in a hot gas flow path (15) extending between a can combustor (2) and a first stage of a turbine (3) in a gas turbine (GT) (9). The combustor transition portion (24) comprises a duct having an upstream end configured for connection to the can combustor (2) and a downstream end configured for connection to the first stage of the turbine (3), wherein the downstream end comprises an outer wall (11), an inner wall (12), a first and a second side wall (21a, 21b). The combustor transition portion is characterized in that at least one side wall (21a, 21b) has a side wall extension portion (20, 20a, 20b), which is extending in a downstream direction beyond an outlet (22). The side wall extension portion (20, 20a, 20b) at least partly encloses a first resonator volume portion (28) and the at least one side wall extension portion (20, 20a, 20b) comprises a resonator hole (26), which is configured as a neck of a Helmholtz-damper. Besides the combustor transition portion (24), a GT comprising such a combustor transition portion (24), a method for retrofitting a GT (9) with such a combustor transition portion (24), and a method for borescope inspection of a GT with such a combustor transition portion are disclosed. |
