Contouring a blade/vane cascade stage

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United States of America Patent

PATENT NO 10648339
APP PUB NO 20180252107A1
SERIAL NO

15908401

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Abstract

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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.

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Patent Owner(s)

Patent OwnerAddress
MTU AERO ENGINES AGMUNICH

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Brettschneider, Markus Karlsfeld, DE 20 67
Maatouk, Fadi Munich, DE 8 22
Mahle, Inga Munich, DE 20 119

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