Flow channel for a turbomachine

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United States of America Patent

PATENT NO 11396812
APP PUB NO 20190169989A1
SERIAL NO

16204954

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ATTORNEY / AGENT: (SPONSORED)

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Abstract

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The present invention relates to a method for designing a flow channel for a turbomachine, in particular a gas turbine that comprises a guide vane cascade having a plurality of guide vanes, which are distributed in the peripheral direction, and flow passages, each of which is bounded by two successive guide vanes, and a support rib arrangement having at least one support rib, wherein a design of one of the flow passages is adapted to this support rib, that it is situated downstream of, in order to reduce a pressure loss and/or a vibrational stimulation.

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Patent Owner(s)

  • MTU AERO ENGINES AG

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Ramm, Guenter Eichenau, DE 11 46

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