Leiteinrichtung fur eine Gasturbine sowie Gasturbine mit einer solchen Leiteinrichtung

摘要

The invention relates to a guide means (10) for a gas turbine, in particular for an aircraft engine, having at least one casing element (12); at least one first duct segment (14), which is arranged in the radial direction on the inside of the casing element (12), by means of which first duct segment, at least one duct (16), through which gas can flow, is at least partially delimited outward in the radial direction; having at least one second duct segment (16), which is arranged in the radial direction on the inside of the first duct segment (14), by means of which second duct segment, the duct (16) is at least partially delimited inward in the radial direction; and having at least one guide vane (28).