| 摘要 |
It is described a gas turbine, comprising: a rotor (2) comprising a rotor portion of a fluid bearing (31) for rotatably supporting the rotor; a radially outer stator portion (18); a radially inner stator portion (16) comprising a stator portion of the fluid bearing; a compressor air passage (10) extending between the radially outer stator portion and the radially inner stator portion; and an annular gap (14) between the rotor and the radially inner stator portion partially forming an annular air passage in communication with the compressor air passage, wherein along a flow direction (43) of air flowing within the annular air passage a radius (r0, r1, r2, r3, r4) of the air passage decreases in a first portion (20, 26) and then increases in a second portion (22, 28). Further a method for operating a gas turbine is described.
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