Patent ID: 7553129

Claim:
A flow structure for 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, wherein the transitional channel comprises an inner wall and an outer wall with supporting ribs positioned in and extending across the transitional channel from the inner wall to the outer wall and arranged so they are spaced a distance apart in a circumferential direction of the transitional channel, wherein at least one guide vane and/or guide rib is positioned between two adjacent supporting ribs which are spaced a distance apart in the circumferential direction of the transitional channel, and wherein a flow outlet edge of the guide rib runs upstream from a flow outlet edge of the supporting ribs, and wherein further the flow outlet edge of the guide rib runs downstream from a flow inlet edge of the supporting ribs.