Gas turbine for aircraft engine, has circular housing area and circular drum area formed as non-immersed layers and provided with thin film layer of specific thickness at surfaces, where film layer is formed without adhesive layers

摘要

The turbine has a compressor (1) consisting of a row of blades (2), where each blade has free ends (3). A thin film layer is formed directly on a circular housing area (4) or at a circular drum area adjacent to the free ends of the blades, where the film layer is formed without adhesive layers. The circular housing area and the circular drum area are formed as non-immersed layers. The thickness of the thin film layer is in the range of 50-150 picometer.