| 摘要 |
The gas turbine has a compressor with a set of blades, where the blades are provided with a free end in each case. An adjacent intake layer (6) is formed on the free end of the blade at a circular housing area. The intake layer is connected with a fluid supplying device (9) and is provided with liquid passage opening. An independent claim is included for a method for running free end area of blades of a compressor of a gas turbine. |
