| 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). |
| 主权项 |
1. A guide means (10) for a gas turbine having at least one casing element (12); having 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 (26), 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), which is arranged at least partially in the duct (16) and which can rotate around an axis of rotation (30) relative to the at least one casing element (12) and relative to the duct segments (14, 26), wherein
the second duct segment (26) is fastened to the guide vane (28) and is retained on the at least one casing element (12) via the guide vane (28), which is mounted on the casing element (12) via a bushing (36), which is inserted in the radial direction from outside to inside into a passage opening (34) of the at least one casing element (12). |
