Gas turbine, has running-in layer connected with material feeder, which contains air-hardening material, where running-in layer is provided with material openings that are formed by pores of material of running-in layer

摘要

The turbine has blades provided with a free end, and a running-in layer (6) formed adjacent to the free end of the blades at a circular housing region (9). The running-in layer is connected with a material feeder (2), which contains an air-hardening material (1). The running-in layer is provided with material openings that are formed by pores of the material of the running-in layer. The running-in layer is arranged in a circular bag of a running-in layer carrier (4), which is provided with recesses (7) for conducting the air-hardening material. An independent claim is also included for a method for running-in of free end regions of blades of a compressor of a gas turbine.