Patent ID: 8720207
Filing Date: 2014-05-13
Classification: F01D,F05D,F23R

Abstract:
1. Gas turbine comprising: an annular combustion chamber defined by an inner wall and an outer wall; a stator airfoil row defined by an annular inner stator wall and an annular outer stator wall housing a plurality of stator airfoils, and at least a rotor airfoil row defined by an annular inner rotor wall and an annular outer rotor wall housing a plurality of rotor airfoils; and a gap between at least one of the inner stator wall and the inner combustion chamber wall, and the outer stator wall and the outer combustion chamber wall, upstream of said stator airfoil row, wherein a border of at least one of the inner and outer stator wall facing the gap is axisymmetric, and a zone of the at least one inner and outer stator wall downstream of the gap and upstream of the stator airfoils is non-axisymmetric and defines bumps arranged to locally increase static pressure of a fluid flow passing through said stator airfoil row to increase uniformity of the static pressure.