PASSAGE CHANNEL FOR A TURBOMACHINE AND TURBOMACHINE
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United States of America Patent
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Issued Date -
Dec 12, 2013
app pub date -
May 29, 2013
filing date -
Jun 1, 2012
priority date (Note) -
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Abstract
A transition duct for a turbomachine, in particular an aircraft engine, for forming a flow channel between an upstream flow cross section and a downstream flow cross section, including supporting ribs which extend between a radially inner duct wall and a radially outer duct wall and each of which has a profile for deflecting a flow from an inlet area to an outlet area of the transition duct, the supporting ribs each having a profile variation in the area of their trailing edge and/or at least one blow-out opening for blowing out a fluid; also disclosed is a turbomachine having a transition duct of this type.
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