| 摘要 |
<p>Gas turbine and method for operating a gas turbine 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; 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); and a discharge conduit (57, 63) for discharging the air flown through the second portion of the annular air passage, wherein an inlet of the discharge conduit for introducing the air flown through the second portion of the annular air passage is axially arranged between the second portion of the annular air passage and the fluid bearing. Further a method for operating a gas turbine is described.</p> |
