Gas turbine and rotor blade for a turbomachine

Details Gas turbine and rotor blade for a turbomachine Gas turbine and rotor blade for a turbomachine

2004-10-04

2008-08-26

Kershteyn, Igor (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Apertured or permeable

C416S23100A

Reexamination Certificate

active

07416394

ABSTRACT:
The invention relates to a rotating blade for a turbomachine which can be cross flown by a flow medium, especially for a gas turbine which can be cross flown by a working fluid. The gas turbine comprises a rotating blade base, a platform region which extends in a perpendicular manner thereto and a curved blade profile all of which are arranged in a successive manner. The blade profile extends from a front edge, against which a liquid can flow, to a rear edge between which a suction side and a pressure side of the blade profile are formed by means of a relief slot comprising a longitudinal extension in the blade profile. In order to produce a rotating blade which has increased durability, the relief slot on the end of the blade profile oriented towards the platform region is arranged in the region of the rear edge, extending through the blade profile from the suction side to the pressure side and the longitudinal extension thereof is oriented in an essentially transversal manner in relation to the direction of flow of the working fluid.

REFERENCES:
patent: 6490791 (2002-12-01), Surace et al.
patent: 6951447 (2005-10-01), Cherolis et al.
patent: 10061406 (1998-03-01), None
patent: 10299408 (1998-11-01), None
patent: 2000018001 (2000-01-01), None
patent: 2000130103 (2000-05-01), None

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