Siemens Energy Global Gmbh & Co. Kg

Marcel Schlösser

Andreas Heselhaus

Ross H Peterson

Andrew Carlson

Markus Gill

Christian Gindorf

Robert Kunte

A rotor blade for a gas turbine, includes a blade extending in a radial direction, with a blade body having a peripheral wall with pressure-side and suction-side wall sections, a plate-shaped crown base connected to the peripheral wall in the region of the blade tip, and a sweep edge extending along the peripheral wall, the peripheral wall and the crown base defining a cavity in the blade body, the sweep edge being aligned on the outer side with the peripheral wall and protruding radially over the crown base, and cooling channels are embodied in the blade body, extending from the cavity to cooling fluid outlets provided in the sweep edge. At least one recess being formed in the front surface of the sweep edge, into which at least some of the cooling channels flow such that the cooling fluid outlets are entirely arranged in a bottom region of the recess.

Growing community of inventors

Mülheim an der Ruhr, Germany

Marcel Schlösser