Contouring a blade/vane cascade stage
AssigneeMTU Aero Engines AG
InventorsInga Mahle, Markus Brettschneider, Fadi Maatouk
Life of this patent
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Abstract
A blade/vane cascade segment for a blade/vane cascade of a turbomachine includes a stage and at least two blade/vane elements that define a blade/vane intermediate strip with an axial cascade span on the stage surface by their leading and trailing edges. A stage edge on the inflow side has a contour with a depression. In the axial direction, this depression extends at most by 10% of the cascade span into the blade/vane intermediate strip. Also provided is a corresponding stage, a blade/vane cascade, a blade/vane channel, and a turbomachine.
Claims14
A blade/vane cascade segment for a blade/vane cascade of a turbomachine, comprising:
- a stage with a stage surface and a stage edge on the inflow side as well as at least two blade/vane elements that define a blade/vane intermediate strip with an axial cascade span on the stage surface by their leading and trailing edges;
- the stage edge on the inflow side has a contour with a depression that extends in an axial direction at most by 10% of the cascade span into the blade/vane intermediate strip.
Dependencies are inferred from the claim text.