Aircraft gas turbine, has connecting area thermally isolated and radially shielded by ring unit against outlet area of compressor plate in flow direction, and impeller and turbine connected with each other using shaft

摘要

The gas turbine has an impeller, and a turbine arranged downstream in a flow direction, where the impeller and the turbine are connected with each other using a circular shaft (3). A connecting area (4) is thermally isolated and radially shielded by a circular ring unit (5) against an air outlet area of a compressor plate (6) in the flow direction. The ring unit is formed as a single unit with the shaft, and is arranged opposite to the flow direction, where the ring unit is formed as a conical ring.