Patent ID: 7517192
Filing Date: 2009-04-14
Classification: F01D,F04D,Y02T

Abstract:
1. A flow structure for a gas turbine, comprising: support ribs arranged in a transition channel and spaced apart from each other around a circumference of the transition channel, the transition channel arranged one of (a) between two compressors, (b) between two turbines, and (c) in a turbine outlet housing downstream from a low-pressure turbine; and at least one of (a) a first channel wall that delimits the transition channel radially on an inside, the first channel wall extending into the transition channel in an area of outflow edges of the support ribs and (b) a second channel wall that delimits the transition channel radially on an outside, the second channel wall extending into the transition channel in an area of outflow edges of the support ribs.