The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Aug. 12, 2014

Filed:

Sep. 28, 2010
Applicants:

Roland Dueckershoff, Hohr-Grenzhausen, DE;

Shailendra Naik, Gebenstorf, CH;

Martin Schnieder, Ennetbaden, CH;

Inventors:

Roland Dueckershoff, Hohr-Grenzhausen, DE;

Shailendra Naik, Gebenstorf, CH;

Martin Schnieder, Ennetbaden, CH;

Assignee:
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 9/02 (2006.01); F01D 9/04 (2006.01); F01D 5/18 (2006.01);
U.S. Cl.
CPC ...
F01D 5/187 (2013.01); F05D 2220/3215 (2013.01); F05D 2250/185 (2013.01); F01D 9/041 (2013.01); Y02T 50/676 (2013.01); F05D 2260/22141 (2013.01); F05D 2260/2212 (2013.01);
Abstract

A stator blade for a gas turbine with sequential combustion, has a blade airfoil which extends in the radial direction between a blade tip and a shroud, with cooling passages extending inside the blade airfoil, through which a cooling medium can flow for cooling the blade and can then discharge from the stator blade into the hot gas flow flowing through the turbine. The blade airfoil has a sharply curved shape in space in the radial direction, and three cooling passages, which extend in the radial direction, arranged inside the blade airfoil in series in the hot gas flow direction and are interconnected by deflection regions, which are arranged at ends of the blade airfoil, so that the cooling medium flows through the cooling passages one after the other, with change of direction. The cooling passages follow the curvature of the blade airfoil in space in the radial direction.


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