Rotor blade for a gas turbine with a cooled sweep edge

US11136892B2 · kind B2 · utility

Assignee

• Siemens Energy Global GmbH & Co. KG · DE

Inventors

• Markus Gill · St. Blasien, DE
• Christian Gindorf · Krefeld, DE
• Andreas Heselhaus · Düsseldorf, DE
• Robert Kunte · Düsseldorf, DE
• Marcel Schlösser · Mülheim an der Ruhr, DE
• Andrew Carlson · North Palm Beach, US
• Ross Peterson · North Palm Beach, US

Key dates

• Filing date: Mar 1, 2017
• Grant date: Oct 5, 2021
• Expiry date: Apr 10, 2038

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2260/202
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

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.