| 摘要 |
A gas turbine (1) comprises an annular combustion chamber (2) defined by an inner wall (3) and an outer wall (4), followed by at least a stator airfoil row (7) defined by an annular inner stator wall (8) and an annular outer stator wall (9) housing a plurality of stator airfoils (10), and at least a rotor airfoil row (11) defined by an annular inner rotor wall (12) and an annular outer rotor wall (13) housing a plurality of rotor airfoils (14). The gas turbine (1) comprises a gap (15, 16) between the inner and/or outer stator wall (8, 9) and the inner and/or outer combustion chamber wall (3, 4), and/or between the inner and/or outer stator wall (8, 9) and/or the inner and/or outer rotor wall 12, 13) of an expansion stage upstream of said stator airfoil row (7). A border (25) of the inner and/or outer stator wall (8, 9) facing the gap (15, 16) is circular in shape. The zone of the inner and/or outer stator wall (8, 9) downstream of the gap (15, 16) and upstream of the stator airfoils (10) is non-axisymmetric and defines bumps (26) arranged to locally increase the static pressure of a fluid flow passing through the stator airfoil row to increase the uniformity of its static pressure.
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