| 摘要 |
For the segmented nozzle ring introduced herewith, the throat area between neighboring vanes is the same for each segment which is achieved by rotation (i.e., opening or closing of the throat area) of the individual vane compounds belonging to the different segments. The resulting uniform throat area leads to a uniform exit flow angle of the nozzle and a uniform inlet flow angle of the rotor. Based on that, high-cycle fatigue excitations of the rotor caused by the non-uniform flow are eliminated, the thermodynamic efficiency of the turbine stage can be improved, and the nozzle ring must not be arranged in a fixed position relative to the gas inlet casing. |
