Blade for a turbomachine, blade arrangement, and turbomachine
AssigneeMTU Aero Engines AG
InventorsMartin Pernleitner, Manfred Dopfer, Norbert Huebner
Life of this patent
Estimating the term…
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.
Claims10
A blade for a turbomachine comprising:
- a shroud having a first lateral edge and a second opposite lateral edge for delimiting a main flow channel;
- and
- a blade extending away from the shroud,
- a transition area encompassing the blade on a root side is guided at least beyond the one lateral edge, a section of the transition area that would protrude beyond the first lateral edge being severed, the severed section situated in the area of the second lateral edge as an elevation offset in the transverse direction.
Dependencies are inferred from the claim text.