| 摘要 |
A turbine engine vane (10) for a gas turbine is disclosed. The turbine engine vane (10), comprises a vane root (11) with a fluid coolant inlet (12), a vane head (13), embodied with a shroud element (14) and a vane blade (15). At least one through channel (19a) is arranged within the vane blade (15), running in the vane longitudinal direction. A shroud cooling channel (22) is embodied in the shroud element over at least a section of the shroud element (14), connected to the through channel (19a) by an opening (23, 24) through which a cooling fluid flows during operation of the turbine engine vane. At least one flow guide element (30, 31 -d1 - 31-d11, 31 -s1 - 31-s12, 32) is arranged in the shroud cooling channel and/or in a inlet or outlet to the shroud cooling channel for guiding at least a part of the cooling fluid flow through the shroud cooling channel. |
