Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Markus Gill

Fathi Ahmad

Andreas Heselhaus

Oliver Schneider

Ross H Peterson

Ralf Müsgen

Andrew Carlson

Silvio-Ulrich Martin

Robert Kunte

Christian Menke

Scarlett Fajardo-Reina

Stefan Werner Kiliani

Christian Gindorf

Marcel Schlösser

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.

Rotor blade for a gas turbine with a cooled sweep edge

A turbine blade has a blade geometry defined in a coordinate system and at least one cavity which is open to the outside and which has a blade internal surface. At least one planar detection surface, which is accessible for the measuring head of a coordinate measuring device, is formed in the blade internal surface, wherein the at least one planar detection surface is assigned a defined design position and/or a defined design orientation with respect to the coordinate system in which the blade geometry is defined.

Turbine blade, method for producing same and method for determining the position of a casting core used when casting a turbine blade

A turbine blade is provided. The turbine blade includes a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure by at least one spacing element. For example the spacing element can be a solder globule in order to form a space through which a cooling medium can flow between the support structure and the shell. A method for the production of a turbine blade having a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure is also provided. The shell is soldered to the support structure in at least at one place of the support structure in order to connect the shell to and at a distance from the support structure.

Turbine blade

Growing community of inventors

Ibbenbüren, Germany

Markus Gill