Coated turbine blade

Details Coated turbine blade Coated turbine blade

2007-08-23

2011-12-13

Look, Edward (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Coating, specific composition or characteristic

C416S233000, C416S23600R

Reexamination Certificate

active

08075279

ABSTRACT:
The invention refers to a coated turbine blade for a gas turbine, having blade walls divided into sections with locally adapted material temperatures. The cooler material temperatures of the blade walls are at the points where the support ribs merge into the blade walls. The regions with higher material temperatures of the blade walls are at the positions where cavities are arranged inside the blade walls. This is achieved via a ceramic thermal barrier coating having different layer thicknesses that allow different material temperatures. The region of the surface of the blade wall which faces the working medium and lies opposite an internal rib has a thicker thermal barrier coating than a region of the surface of the blade wall which is cooled via a cooling medium that flows in the cavities. This results in homogenization of the material temperature in the connecting regions, which results in prolonged blade life.

REFERENCES:
patent: 4643647 (1987-02-01), Perry
patent: 5690473 (1997-11-01), Kercher
patent: 5913661 (1999-06-01), Panovsky et al.
patent: 7845905 (2010-12-01), Ahmad et al.
patent: 0 139 396 (1985-05-01), None
patent: WO 00/12868 (2000-03-01), None
patent: WO 00/25005 (2000-05-01), None

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