Is a
Patent attributes
Current Assignee
Patent Jurisdiction
Patent Number
Date of Patent
June 30, 2009
Patent Application Number
11190447
Date Filed
July 27, 2005
Patent Citations Received
Patent Primary Examiner
Patent abstract
A flow structure of a gas turbine, in particular for an aircraft engine, in a transitional channel between two compressors or in a transitional channel between two turbines or in a transitional channel of a turbine outlet housing downstream from a low-pressure turbine is disclosed. Supporting ribs are positioned in the transitional channel and spaced a distance apart in the circumferential direction of the transitional channel. At least one guide vane and/or guide rib is positioned between two supporting ribs spaced a distance apart from one another. The flow outlet edge of the guide rib or each guide rib runs upstream from the flow outlet edges of the supporting ribs.
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