Gas turbine blade i.e. compressor blade, has platforms supporting turbine blade and connected with disk, where outer contour of one platform runs parallel to outer contour of turbine blade

摘要

The blade has platforms (1) supporting a turbine blade (2), and connected with a disk (4) in radial direction and circumferential direction of the disk by a root (3). The platforms adjacent to the circumferential direction are provided with outer contours which are matched with each. The outer contour of one platform runs parallel to an outer contour of the turbine blade. The outer contour of the platform runs in direction of surface-near current of the turbine blade, and runs in direction of gas flow along the platform.