Axial flow turbo compressor for a gas turbine with a diffuser low loss and low-loss gap

摘要

The present invention relates to axial turbo-compressors for gas turbines, the turbo-compressor, exposed to the hub side, the vane tip (4) stator vane assembly formed by the stator vane (3) provided with a (2) , disposed directly adjacent to the hub side vane tip (4), and a stationary shaft cover defining a flow path of axial turbocompressor (1) (6) comprises a shaft cover radially gap designed between (6) and the vane tip (4), the gap, the assembly is capable of is barely assembly and the plurality of depressions in the axial turbocompressor (1) (7) of the shaft cover (6) are minimized to be present, one of the recesses (7) is assigned to each of the vane tip (4), disposed directly adjacent to the assigned vane tip (4) and the shaft subducts flow each vane tip (4) corresponds recess (7) in the time of operation of the turbo compressor (1), as one of the vane tip (4) which does not significantly contact with the shaft cover (6) It is assigned to.