Alstom Technology Limited

Ansaldo Energia Switzerland Ag

Christian Sommer

Shailendra Naik

Willy Heinz Hofmann

Ulrich Robert Steiger

Frank Gersbach

An airfoil for a working fluid path of a turboengine extends along a spanwidth direction from a base to a tip. An aerodynamic body thereof includes a suction side surface, a pressure side surface, a leading edge, a trailing edge and a tip, the tip of the aerodynamic body having a tip cross section and a cross-sectional contour circumscribing the tip cross section. A rim extends to the tip of the airfoil and follows the cross-sectional contour on the pressure side, the suction side and extends over the leading edge of the airfoil, the rim delimiting a tip cavity which is open at the tip of the airfoil. The rim is further open at the trailing edge of the airfoil such that the tip cavity is open at the trailing edge of the airfoil.

Airfoil having a tip capacity

A gas turbine is disclosed which includes an annular combustion chamber defined by an inner wall and an outer wall. A stator airfoil row can be 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. A gap is arranged, for example, 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. A border of at least one of the inner and outer stator wall facing the gap can be axisymmetric. A zone of at least one of the inner and outer stator wall downstream of the gap and upstream of the stator airfoils can be non-axisymmetric and defines bumps arranged to locally increase the static pressure of a fluid flow passing through said stator airfoil row to increase the uniformity of the static pressure.

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Nussbaumen, Switzerland

Christian Sommer