Blade for a turbomachine, blade arrangement, and turbomachine
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United States of America Patent
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Jun 7, 2016
Grant Date -
Oct 17, 2013
app pub date -
Apr 12, 2013
filing date -
Apr 13, 2012
priority date (Note) -
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Abstract
A blade for a turbomachine, in particular a jet engine, including a shroud, having two opposite lateral edges, for delimiting a main flow channel and including a blade which extends away from the shroud, a rounded transition area being provided which encompasses the blade on its root side and is guided beyond the one lateral edge, a section of the transition area protruding beyond the one lateral edge being severed and situated in the area of the other lateral edge as an elevation offset in the transverse direction, a blade arrangement having at least two of such blades as well as a turbomachine having a plurality of such blades.
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