Drilled cooling air openings in gas turbine components

US6439848B2 · kind B2 · utility

Assignee

• ALSTOM (Switzerland) Ltd · CH

Inventors

• Hartmut Haehnle · Waldshut-Tiengen, DE
• Bernhard Weigand · Lauchringen, DE

Key dates

• Filing date: Dec 19, 2000
• Grant date: Aug 27, 2002
• Expiry date: Dec 19, 2020

Classification

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

Abstract

A blade component of a gas turbine is disclosed around the outside of which hot air flows. The blade component is constructed as a hollow profile having outside walls and a tip cover, and having guiding walls arranged between the outside walls and connecting said outside walls. The blade component is cooled on the inside by cooling air flowing through cooling channels between the outside walls and the guiding walls. Cooling air flows through deflection areas in which the cooling air is deflected into flow stagnation zones. An efficient cooling of the blade component in the area of the stagnation zones is obtained in the area of the flow stagnation zones which are located at the outer corner of the deflection area. At least one drilled opening is provided in the outside wall through which drilled opening cooling air is able to flow at the stagnation zone from the cooling channel onto the outside of the blade component.