| 摘要 |
<p>A rotor blade for fastening on the rotor of a turbomachine, especially of a compressor of a gas turbine, comprises a blade airfoil and a blade root (15) which adjoins the lower end of the blade airfoil and extends along a blade axis and by which the rotor blade, in an encompassing slot which is arranged on the outer periphery of the rotor, is retained between two spacers (12, 18) which follow each other in the circumferential direction and which in their turn are retained in the slot, wherein the blade root (15) is formed with a T-shape in cross section and by shoulders (16, 16') which extend in the circumferential direction fits under the adjacent spacers (12, 18), and the spacers (12, 18), in the direction of the blade axis, engage by retaining surfaces (20) in undercuts (24) in the slot. A reduced production cost with comparable service life is achieved by the T-shaped blade root (15) being milled, and, for reducing the mechanical stresses at the transitions of the blade root (15) to the shoulders (16, 16'), by a relief groove (21), which extends in the direction of the blade axis, being provided in each case.</p> |
