Flow structure for a gas turbine

Details Flow structure for a gas turbine Flow structure for a gas turbine

2005-07-27

2009-06-30

Nguyen, Ninh H (Department: 3745)

Rotary kinetic fluid motors or pumps

Working fluid passage or distributing means associated with...

Plural distributing means immediately upstream of runner

C415S194000, C415S209100, C415S211200

Reexamination Certificate

active

07553129

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.

REFERENCES:
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patent: 6905303 (2005-06-01), Liu et al.
patent: 7258525 (2007-08-01), Boeck
patent: 2004/0101405 (2004-05-01), Turner et al.
patent: 2005/0175448 (2005-08-01), Jacobsson

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